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RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Fig. 2A illustrates a rocket with the CP, CG locations reversed, that is, the CP is ahead of the CG. This is an undesirable scenario.In this figure, the rocket is initially stable, being in the same ideal situation as in Fig. 1A, with no perturbing forces present. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Preparation and Mixing. The first step in preparation of the propellant is to grind, or mill, the potassium nitrate to a fine texture. This may easily be done with the use of an electric coffee grinder, such as that shown in Figure 2. SIMPLIFIED METHOD FOR ESTIMATING THE FLIGHT PERFORMANCE OF Author: Richard A. Nakka February 2007 Rev.1 March 2007 3 m g F z z 1 2 = Peak altitude, zero drag 2 ( )z2 z1 g 2 t =t + − Time to apogee, zero drag In reality, aerodynamic drag will reduce the flight performance of the rocket RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEHYDRAULIC LOAD CELL FOR THRUST MEASUREMENTRADIO TRANSMITTERTHEORY APPENDICES November 9, 2020-- Over the past year I have been experimenting with a promising new variant of the classic Potassium Nitrate/Sorbitol (KNSB) propellant.This new propellant, which I've denoted KNPSB, utilizes potassium perchlorate (commonly abbreviated KP) as a supplemental oxidizer.The KP content serves to significantly boost the performance, and as an unexpected bonus, RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE I spent an enjoyable summer and fall of 1971 building and flying model "kit" rockets powered by commercial model rocket motors.This was my first foray into rocketry and I soon found that this hobby was an exciting and challenging one. I learned the basics of aerodynamics, stability, motor ignition, safe recovery, tracking and organizing. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Rocket motors. It is expected that the Impulser-X motor will be used for most initial flights. Plans are in the works for flights powered by the new Helios-XX "I-class" motor powered by ANCP, which has a similar total impulse as Impulser-X.Another motor that is slated to loft the Xi rocket is the SSJ-F motor, a "J-class" motor that is the flight version of the SSJ motor that was used for RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Richard Nakka's. Experimental Rocketry. Web Site. The convective heat transfer coefficient, h, relates the amount of heat transferred between a moving bulk fluid (liquid or gas) and a bounding surface. The moving fluid itself offers no resistance to heat transmission, rather, a thin film of fluid adjacent to the wall offers resistance. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Introduction. There are certainly countless solid propellant formulations that have been tried by amateur experimentalists over the years.Some have been very successful and have gained worldwide popularity, although undoubtedly most formulations have been simply downright failures, or at RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Example. The pressure-time data from a static test of the APM-C.2 rocket motor will be used to obtain the propellant burn rate and burn rate parameters a and n.The APM-C.2 is a 51mm experimental rocket motor powered by the newly-developed KNPSB propellant.. After obtaining the burn rate parameters, these are inputted into SRM.XLS rocket motor design software, and the prediction for chamber RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Propellant Formulation. The standard formulation of KNSB propellant is 65% potassium nitrate (KN) which serves as the oxidizer and 35% Sorbitol (SB) which serves as the fuel and binder. This ratio of oxidizer to fuel mass represents a practical upper limit for "solids" loading of a sugar binder, while maintaining good performance and burn rate characteristics. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE This is an illustration of what is referred to as a pyrotechnic igniter which was used for igniting the B-200, C-400 and similar sugar-propellant rocket motors.It consists of a length of polyethylene plastic drinking straw filled as shown with a charge of Ignition Powder, and as such, is often referred to as a "straw igniter".. The igniter is sealed at both ends with polyethylene "hot-melt glue". RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEBEST FINS FOR BOTTLE ROCKETBOTTLE ROCKET FIN DESIGNSFINS ON A ROCKET DEFINITIONMODEL ROCKET FINSBOTTLE ROCKET FIN TEMPLATEROCKET FINS DESIGN Fig. 2A illustrates a rocket with the CP, CG locations reversed, that is, the CP is ahead of the CG. This is an undesirable scenario.In this figure, the rocket is initially stable, being in the same ideal situation as in Fig. 1A, with no perturbing forces present. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Second from left is the sample for testing the longitudinal strength of the panel seam joints (panels are joined with seam binding). In the centre is one of the test RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEHYDRAULIC LOAD CELL FOR THRUST MEASUREMENTRADIO TRANSMITTERTHEORY APPENDICES November 9, 2020-- Over the past year I have been experimenting with a promising new variant of the classic Potassium Nitrate/Sorbitol (KNSB) propellant.This new propellant, which I've denoted KNPSB, utilizes potassium perchlorate (commonly abbreviated KP) as a supplemental oxidizer.The KP content serves to significantly boost the performance, and as an unexpected bonus, RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE I spent an enjoyable summer and fall of 1971 building and flying model "kit" rockets powered by commercial model rocket motors.This was my first foray into rocketry and I soon found that this hobby was an exciting and challenging one. I learned the basics of aerodynamics, stability, motor ignition, safe recovery, tracking and organizing. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Rocket motors. It is expected that the Impulser-X motor will be used for most initial flights. Plans are in the works for flights powered by the new Helios-XX "I-class" motor powered by ANCP, which has a similar total impulse as Impulser-X.Another motor that is slated to loft the Xi rocket is the SSJ-F motor, a "J-class" motor that is the flight version of the SSJ motor that was used for RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Richard Nakka's. Experimental Rocketry. Web Site. The convective heat transfer coefficient, h, relates the amount of heat transferred between a moving bulk fluid (liquid or gas) and a bounding surface. The moving fluid itself offers no resistance to heat transmission, rather, a thin film of fluid adjacent to the wall offers resistance. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Introduction. There are certainly countless solid propellant formulations that have been tried by amateur experimentalists over the years.Some have been very successful and have gained worldwide popularity, although undoubtedly most formulations have been simply downright failures, or at RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Example. The pressure-time data from a static test of the APM-C.2 rocket motor will be used to obtain the propellant burn rate and burn rate parameters a and n.The APM-C.2 is a 51mm experimental rocket motor powered by the newly-developed KNPSB propellant.. After obtaining the burn rate parameters, these are inputted into SRM.XLS rocket motor design software, and the prediction for chamber RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Propellant Formulation. The standard formulation of KNSB propellant is 65% potassium nitrate (KN) which serves as the oxidizer and 35% Sorbitol (SB) which serves as the fuel and binder. This ratio of oxidizer to fuel mass represents a practical upper limit for "solids" loading of a sugar binder, while maintaining good performance and burn rate characteristics. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE This is an illustration of what is referred to as a pyrotechnic igniter which was used for igniting the B-200, C-400 and similar sugar-propellant rocket motors.It consists of a length of polyethylene plastic drinking straw filled as shown with a charge of Ignition Powder, and as such, is often referred to as a "straw igniter".. The igniter is sealed at both ends with polyethylene "hot-melt glue". RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEBEST FINS FOR BOTTLE ROCKETBOTTLE ROCKET FIN DESIGNSFINS ON A ROCKET DEFINITIONMODEL ROCKET FINSBOTTLE ROCKET FIN TEMPLATEROCKET FINS DESIGN Fig. 2A illustrates a rocket with the CP, CG locations reversed, that is, the CP is ahead of the CG. This is an undesirable scenario.In this figure, the rocket is initially stable, being in the same ideal situation as in Fig. 1A, with no perturbing forces present. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Second from left is the sample for testing the longitudinal strength of the panel seam joints (panels are joined with seam binding). In the centre is one of the test RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE This is an illustration of what is referred to as a pyrotechnic igniter which was used for igniting the B-200, C-400 and similar sugar-propellant rocket motors.It consists of a length of polyethylene plastic drinking straw filled as shown with a charge of Ignition Powder, and as such, is often referred to as a "straw igniter".. The igniter is sealed at both ends with polyethylene "hot-melt glue". RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE The gliding nature of a parachute is another reason that using Cd as a measure of the effectiveness of a parachute can be misleading (Fig. 1). When a parachute descends, it may have both a downward component of velocity as well as a horizontal component (in other words, rather than descending straight down, it will descend at an angle).Air flowing around the parachute at a certain velocity (V RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE An alternate non-metal material that is especially suitable is graphite, although the use of this material requires special considerations, due to the copious amount of messy and electrically conductive dust that is generated. An old shop-vac with a very fine dust filter works well to draw away the dust as it is produced. Graphite nozzles are ideal for use with high combustion temperature RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Conclusions The most effective inhibitor was the polyester resin impregnated cotton (followed closely by the epoxy resin impregnated cotton).This result is interesting, because the polyester/cotton inhibitor was chosen as the inhibitor material for the Kappa rocket motor grain, after an earlier investigation demonstrated its effectiveness (see Investigation of Polyester Coating for Ablative RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Specific Impulse. The Specific Impulse that a propellant is capable of producing (either theoretical or "delivered") is the key "yardstick" of performance potential. In its basic form, Specific Impulse can be considered to relate the thrust produced by a unit mass (e.g. 1 lb or kg) of propellant over a burning time of one second.As such, the units of Specific Impulse would be lb-s/lb or N-s/kg. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE SRM.XLS Solid Rocket Motor Design SRM.xls is an MS EXCEL spreadsheet that takes user-inputted motor and grain geometry data and computes Kn over the duration of the motor burn, generates a pressure-time curve, a thrust-time curve, as well as performance parameters such as total impulse and delivered specific impulse. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Technical Notepad #5 -- KNER Ideal Performance Calculations. Note 1 . Potassium Nitrate - Erythritol (KNER) propellant 65/35 O/F ratio @ 1000 psia chamber pressure RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE 80grams NH 4 NO 3 + 56.1grams KOH -> 17grams NH 3 + 18grams H 2 O + 101.1grams KNO 3. It can be seen that "mass is conserved", that is, the total mass of the reactants (136.1g) is equal to the total mass of the products (136.1g). RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Static Test Rig The newly built STS-5000 Static Test Rig was used for the first time with this test. Both thrust and chamber pressure were measured. Thrust was measured by use of a hydraulic load cell connected to a 4" 0-1000 psi pressure gauge. To measure chamber pressure, the motor bulkhead was tapped with a pressure fitting which was connected to a 4" 0-2000 psi gauge. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Preparation and Mixing. The first step in preparation of the propellant is to grind, or mill, the potassium nitrate to a fine texture. This may easily be done with the use of an electric coffee grinder, such as that shown in Figure 2. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEHYDRAULIC LOAD CELL FOR THRUST MEASUREMENTRADIO TRANSMITTERTHEORY APPENDICES November 9, 2020-- Over the past year I have been experimenting with a promising new variant of the classic Potassium Nitrate/Sorbitol (KNSB) propellant.This new propellant, which I've denoted KNPSB, utilizes potassium perchlorate (commonly abbreviated KP) as a supplemental oxidizer.The KP content serves to significantly boost the performance, and as an unexpected bonus, RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE I spent an enjoyable summer and fall of 1971 building and flying model "kit" rockets powered by commercial model rocket motors.This was my first foray into rocketry and I soon found that this hobby was an exciting and challenging one. I learned the basics of aerodynamics, stability, motor ignition, safe recovery, tracking and organizing. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Rocket motors. It is expected that the Impulser-X motor will be used for most initial flights. Plans are in the works for flights powered by the new Helios-XX "I-class" motor powered by ANCP, which has a similar total impulse as Impulser-X.Another motor that is slated to loft the Xi rocket is the SSJ-F motor, a "J-class" motor that is the flight version of the SSJ motor that was used for RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Richard Nakka's. Experimental Rocketry. Web Site. The convective heat transfer coefficient, h, relates the amount of heat transferred between a moving bulk fluid (liquid or gas) and a bounding surface. The moving fluid itself offers no resistance to heat transmission, rather, a thin film of fluid adjacent to the wall offers resistance. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Introduction. There are certainly countless solid propellant formulations that have been tried by amateur experimentalists over the years.Some have been very successful and have gained worldwide popularity, although undoubtedly most formulations have been simply downright failures, or at RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Example. The pressure-time data from a static test of the APM-C.2 rocket motor will be used to obtain the propellant burn rate and burn rate parameters a and n.The APM-C.2 is a 51mm experimental rocket motor powered by the newly-developed KNPSB propellant.. After obtaining the burn rate parameters, these are inputted into SRM.XLS rocket motor design software, and the prediction for chamber RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Propellant Formulation. The standard formulation of KNSB propellant is 65% potassium nitrate (KN) which serves as the oxidizer and 35% Sorbitol (SB) which serves as the fuel and binder. This ratio of oxidizer to fuel mass represents a practical upper limit for "solids" loading of a sugar binder, while maintaining good performance and burn rate characteristics. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE This is an illustration of what is referred to as a pyrotechnic igniter which was used for igniting the B-200, C-400 and similar sugar-propellant rocket motors.It consists of a length of polyethylene plastic drinking straw filled as shown with a charge of Ignition Powder, and as such, is often referred to as a "straw igniter".. The igniter is sealed at both ends with polyethylene "hot-melt glue". RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEBEST FINS FOR BOTTLE ROCKETBOTTLE ROCKET FIN DESIGNSFINS ON A ROCKET DEFINITIONMODEL ROCKET FINSBOTTLE ROCKET FIN TEMPLATEROCKET FINS DESIGN Fig. 2A illustrates a rocket with the CP, CG locations reversed, that is, the CP is ahead of the CG. This is an undesirable scenario.In this figure, the rocket is initially stable, being in the same ideal situation as in Fig. 1A, with no perturbing forces present. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Second from left is the sample for testing the longitudinal strength of the panel seam joints (panels are joined with seam binding). In the centre is one of the test RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEHYDRAULIC LOAD CELL FOR THRUST MEASUREMENTRADIO TRANSMITTERTHEORY APPENDICES November 9, 2020-- Over the past year I have been experimenting with a promising new variant of the classic Potassium Nitrate/Sorbitol (KNSB) propellant.This new propellant, which I've denoted KNPSB, utilizes potassium perchlorate (commonly abbreviated KP) as a supplemental oxidizer.The KP content serves to significantly boost the performance, and as an unexpected bonus, RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE I spent an enjoyable summer and fall of 1971 building and flying model "kit" rockets powered by commercial model rocket motors.This was my first foray into rocketry and I soon found that this hobby was an exciting and challenging one. I learned the basics of aerodynamics, stability, motor ignition, safe recovery, tracking and organizing. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Rocket motors. It is expected that the Impulser-X motor will be used for most initial flights. Plans are in the works for flights powered by the new Helios-XX "I-class" motor powered by ANCP, which has a similar total impulse as Impulser-X.Another motor that is slated to loft the Xi rocket is the SSJ-F motor, a "J-class" motor that is the flight version of the SSJ motor that was used for RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Richard Nakka's. Experimental Rocketry. Web Site. The convective heat transfer coefficient, h, relates the amount of heat transferred between a moving bulk fluid (liquid or gas) and a bounding surface. The moving fluid itself offers no resistance to heat transmission, rather, a thin film of fluid adjacent to the wall offers resistance. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Introduction. There are certainly countless solid propellant formulations that have been tried by amateur experimentalists over the years.Some have been very successful and have gained worldwide popularity, although undoubtedly most formulations have been simply downright failures, or at RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Example. The pressure-time data from a static test of the APM-C.2 rocket motor will be used to obtain the propellant burn rate and burn rate parameters a and n.The APM-C.2 is a 51mm experimental rocket motor powered by the newly-developed KNPSB propellant.. After obtaining the burn rate parameters, these are inputted into SRM.XLS rocket motor design software, and the prediction for chamber RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Propellant Formulation. The standard formulation of KNSB propellant is 65% potassium nitrate (KN) which serves as the oxidizer and 35% Sorbitol (SB) which serves as the fuel and binder. This ratio of oxidizer to fuel mass represents a practical upper limit for "solids" loading of a sugar binder, while maintaining good performance and burn rate characteristics. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE This is an illustration of what is referred to as a pyrotechnic igniter which was used for igniting the B-200, C-400 and similar sugar-propellant rocket motors.It consists of a length of polyethylene plastic drinking straw filled as shown with a charge of Ignition Powder, and as such, is often referred to as a "straw igniter".. The igniter is sealed at both ends with polyethylene "hot-melt glue". RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEBEST FINS FOR BOTTLE ROCKETBOTTLE ROCKET FIN DESIGNSFINS ON A ROCKET DEFINITIONMODEL ROCKET FINSBOTTLE ROCKET FIN TEMPLATEROCKET FINS DESIGN Fig. 2A illustrates a rocket with the CP, CG locations reversed, that is, the CP is ahead of the CG. This is an undesirable scenario.In this figure, the rocket is initially stable, being in the same ideal situation as in Fig. 1A, with no perturbing forces present. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Second from left is the sample for testing the longitudinal strength of the panel seam joints (panels are joined with seam binding). In the centre is one of the test RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE This is an illustration of what is referred to as a pyrotechnic igniter which was used for igniting the B-200, C-400 and similar sugar-propellant rocket motors.It consists of a length of polyethylene plastic drinking straw filled as shown with a charge of Ignition Powder, and as such, is often referred to as a "straw igniter".. The igniter is sealed at both ends with polyethylene "hot-melt glue". RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE The gliding nature of a parachute is another reason that using Cd as a measure of the effectiveness of a parachute can be misleading (Fig. 1). When a parachute descends, it may have both a downward component of velocity as well as a horizontal component (in other words, rather than descending straight down, it will descend at an angle).Air flowing around the parachute at a certain velocity (V RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE An alternate non-metal material that is especially suitable is graphite, although the use of this material requires special considerations, due to the copious amount of messy and electrically conductive dust that is generated. An old shop-vac with a very fine dust filter works well to draw away the dust as it is produced. Graphite nozzles are ideal for use with high combustion temperature RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Conclusions The most effective inhibitor was the polyester resin impregnated cotton (followed closely by the epoxy resin impregnated cotton).This result is interesting, because the polyester/cotton inhibitor was chosen as the inhibitor material for the Kappa rocket motor grain, after an earlier investigation demonstrated its effectiveness (see Investigation of Polyester Coating for Ablative RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Specific Impulse. The Specific Impulse that a propellant is capable of producing (either theoretical or "delivered") is the key "yardstick" of performance potential. In its basic form, Specific Impulse can be considered to relate the thrust produced by a unit mass (e.g. 1 lb or kg) of propellant over a burning time of one second.As such, the units of Specific Impulse would be lb-s/lb or N-s/kg. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE SRM.XLS Solid Rocket Motor Design SRM.xls is an MS EXCEL spreadsheet that takes user-inputted motor and grain geometry data and computes Kn over the duration of the motor burn, generates a pressure-time curve, a thrust-time curve, as well as performance parameters such as total impulse and delivered specific impulse. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Technical Notepad #5 -- KNER Ideal Performance Calculations. Note 1 . Potassium Nitrate - Erythritol (KNER) propellant 65/35 O/F ratio @ 1000 psia chamber pressure RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE 80grams NH 4 NO 3 + 56.1grams KOH -> 17grams NH 3 + 18grams H 2 O + 101.1grams KNO 3. It can be seen that "mass is conserved", that is, the total mass of the reactants (136.1g) is equal to the total mass of the products (136.1g). RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Static Test Rig The newly built STS-5000 Static Test Rig was used for the first time with this test. Both thrust and chamber pressure were measured. Thrust was measured by use of a hydraulic load cell connected to a 4" 0-1000 psi pressure gauge. To measure chamber pressure, the motor bulkhead was tapped with a pressure fitting which was connected to a 4" 0-2000 psi gauge. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Preparation and Mixing. The first step in preparation of the propellant is to grind, or mill, the potassium nitrate to a fine texture. This may easily be done with the use of an electric coffee grinder, such as that shown in Figure 2. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEHYDRAULIC LOAD CELL FOR THRUST MEASUREMENTRADIO TRANSMITTERTHEORY APPENDICES November 9, 2020-- Over the past year I have been experimenting with a promising new variant of the classic Potassium Nitrate/Sorbitol (KNSB) propellant.This new propellant, which I've denoted KNPSB, utilizes potassium perchlorate (commonly abbreviated KP) as a supplemental oxidizer.The KP content serves to significantly boost the performance, and as an unexpected bonus, RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE I spent an enjoyable summer and fall of 1971 building and flying model "kit" rockets powered by commercial model rocket motors.This was my first foray into rocketry and I soon found that this hobby was an exciting and challenging one. I learned the basics of aerodynamics, stability, motor ignition, safe recovery, tracking and organizing. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Rocket motors. It is expected that the Impulser-X motor will be used for most initial flights. Plans are in the works for flights powered by the new Helios-XX "I-class" motor powered by ANCP, which has a similar total impulse as Impulser-X.Another motor that is slated to loft the Xi rocket is the SSJ-F motor, a "J-class" motor that is the flight version of the SSJ motor that was used for RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Richard Nakka's. Experimental Rocketry. Web Site. The convective heat transfer coefficient, h, relates the amount of heat transferred between a moving bulk fluid (liquid or gas) and a bounding surface. The moving fluid itself offers no resistance to heat transmission, rather, a thin film of fluid adjacent to the wall offers resistance. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Introduction. There are certainly countless solid propellant formulations that have been tried by amateur experimentalists over the years.Some have been very successful and have gained worldwide popularity, although undoubtedly most formulations have been simply downright failures, or at RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Example. The pressure-time data from a static test of the APM-C.2 rocket motor will be used to obtain the propellant burn rate and burn rate parameters a and n.The APM-C.2 is a 51mm experimental rocket motor powered by the newly-developed KNPSB propellant.. After obtaining the burn rate parameters, these are inputted into SRM.XLS rocket motor design software, and the prediction for chamber RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Propellant Formulation. The standard formulation of KNSB propellant is 65% potassium nitrate (KN) which serves as the oxidizer and 35% Sorbitol (SB) which serves as the fuel and binder. This ratio of oxidizer to fuel mass represents a practical upper limit for "solids" loading of a sugar binder, while maintaining good performance and burn rate characteristics. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE This is an illustration of what is referred to as a pyrotechnic igniter which was used for igniting the B-200, C-400 and similar sugar-propellant rocket motors.It consists of a length of polyethylene plastic drinking straw filled as shown with a charge of Ignition Powder, and as such, is often referred to as a "straw igniter".. The igniter is sealed at both ends with polyethylene "hot-melt glue". RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEBEST FINS FOR BOTTLE ROCKETBOTTLE ROCKET FIN DESIGNSFINS ON A ROCKET DEFINITIONMODEL ROCKET FINSBOTTLE ROCKET FIN TEMPLATEROCKET FINS DESIGN Fig. 2A illustrates a rocket with the CP, CG locations reversed, that is, the CP is ahead of the CG. This is an undesirable scenario.In this figure, the rocket is initially stable, being in the same ideal situation as in Fig. 1A, with no perturbing forces present. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Second from left is the sample for testing the longitudinal strength of the panel seam joints (panels are joined with seam binding). In the centre is one of the test RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEHYDRAULIC LOAD CELL FOR THRUST MEASUREMENTRADIO TRANSMITTERTHEORY APPENDICES November 9, 2020-- Over the past year I have been experimenting with a promising new variant of the classic Potassium Nitrate/Sorbitol (KNSB) propellant.This new propellant, which I've denoted KNPSB, utilizes potassium perchlorate (commonly abbreviated KP) as a supplemental oxidizer.The KP content serves to significantly boost the performance, and as an unexpected bonus, RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE I spent an enjoyable summer and fall of 1971 building and flying model "kit" rockets powered by commercial model rocket motors.This was my first foray into rocketry and I soon found that this hobby was an exciting and challenging one. I learned the basics of aerodynamics, stability, motor ignition, safe recovery, tracking and organizing. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Rocket motors. It is expected that the Impulser-X motor will be used for most initial flights. Plans are in the works for flights powered by the new Helios-XX "I-class" motor powered by ANCP, which has a similar total impulse as Impulser-X.Another motor that is slated to loft the Xi rocket is the SSJ-F motor, a "J-class" motor that is the flight version of the SSJ motor that was used for RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Richard Nakka's. Experimental Rocketry. Web Site. The convective heat transfer coefficient, h, relates the amount of heat transferred between a moving bulk fluid (liquid or gas) and a bounding surface. The moving fluid itself offers no resistance to heat transmission, rather, a thin film of fluid adjacent to the wall offers resistance. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Introduction. There are certainly countless solid propellant formulations that have been tried by amateur experimentalists over the years.Some have been very successful and have gained worldwide popularity, although undoubtedly most formulations have been simply downright failures, or at RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Example. The pressure-time data from a static test of the APM-C.2 rocket motor will be used to obtain the propellant burn rate and burn rate parameters a and n.The APM-C.2 is a 51mm experimental rocket motor powered by the newly-developed KNPSB propellant.. After obtaining the burn rate parameters, these are inputted into SRM.XLS rocket motor design software, and the prediction for chamber RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Propellant Formulation. The standard formulation of KNSB propellant is 65% potassium nitrate (KN) which serves as the oxidizer and 35% Sorbitol (SB) which serves as the fuel and binder. This ratio of oxidizer to fuel mass represents a practical upper limit for "solids" loading of a sugar binder, while maintaining good performance and burn rate characteristics. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE This is an illustration of what is referred to as a pyrotechnic igniter which was used for igniting the B-200, C-400 and similar sugar-propellant rocket motors.It consists of a length of polyethylene plastic drinking straw filled as shown with a charge of Ignition Powder, and as such, is often referred to as a "straw igniter".. The igniter is sealed at both ends with polyethylene "hot-melt glue". RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITEBEST FINS FOR BOTTLE ROCKETBOTTLE ROCKET FIN DESIGNSFINS ON A ROCKET DEFINITIONMODEL ROCKET FINSBOTTLE ROCKET FIN TEMPLATEROCKET FINS DESIGN Fig. 2A illustrates a rocket with the CP, CG locations reversed, that is, the CP is ahead of the CG. This is an undesirable scenario.In this figure, the rocket is initially stable, being in the same ideal situation as in Fig. 1A, with no perturbing forces present. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY WEB SITE Second from left is the sample for testing the longitudinal strength of the panel seam joints (panels are joined with seam binding). In the centre is one of the test RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE This is an illustration of what is referred to as a pyrotechnic igniter which was used for igniting the B-200, C-400 and similar sugar-propellant rocket motors.It consists of a length of polyethylene plastic drinking straw filled as shown with a charge of Ignition Powder, and as such, is often referred to as a "straw igniter".. The igniter is sealed at both ends with polyethylene "hot-melt glue". RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE The gliding nature of a parachute is another reason that using Cd as a measure of the effectiveness of a parachute can be misleading (Fig. 1). When a parachute descends, it may have both a downward component of velocity as well as a horizontal component (in other words, rather than descending straight down, it will descend at an angle).Air flowing around the parachute at a certain velocity (V RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE An alternate non-metal material that is especially suitable is graphite, although the use of this material requires special considerations, due to the copious amount of messy and electrically conductive dust that is generated. An old shop-vac with a very fine dust filter works well to draw away the dust as it is produced. Graphite nozzles are ideal for use with high combustion temperature RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Conclusions The most effective inhibitor was the polyester resin impregnated cotton (followed closely by the epoxy resin impregnated cotton).This result is interesting, because the polyester/cotton inhibitor was chosen as the inhibitor material for the Kappa rocket motor grain, after an earlier investigation demonstrated its effectiveness (see Investigation of Polyester Coating for Ablative RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Specific Impulse. The Specific Impulse that a propellant is capable of producing (either theoretical or "delivered") is the key "yardstick" of performance potential. In its basic form, Specific Impulse can be considered to relate the thrust produced by a unit mass (e.g. 1 lb or kg) of propellant over a burning time of one second.As such, the units of Specific Impulse would be lb-s/lb or N-s/kg. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE SRM.XLS Solid Rocket Motor Design SRM.xls is an MS EXCEL spreadsheet that takes user-inputted motor and grain geometry data and computes Kn over the duration of the motor burn, generates a pressure-time curve, a thrust-time curve, as well as performance parameters such as total impulse and delivered specific impulse. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Technical Notepad #5 -- KNER Ideal Performance Calculations. Note 1 . Potassium Nitrate - Erythritol (KNER) propellant 65/35 O/F ratio @ 1000 psia chamber pressure RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE 80grams NH 4 NO 3 + 56.1grams KOH -> 17grams NH 3 + 18grams H 2 O + 101.1grams KNO 3. It can be seen that "mass is conserved", that is, the total mass of the reactants (136.1g) is equal to the total mass of the products (136.1g). RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Static Test Rig The newly built STS-5000 Static Test Rig was used for the first time with this test. Both thrust and chamber pressure were measured. Thrust was measured by use of a hydraulic load cell connected to a 4" 0-1000 psi pressure gauge. To measure chamber pressure, the motor bulkhead was tapped with a pressure fitting which was connected to a 4" 0-2000 psi gauge. RICHARD NAKKA'S EXPERIMENTAL ROCKETRY SITE Preparation and Mixing. The first step in preparation of the propellant is to grind, or mill, the potassium nitrate to a fine texture. This may easily be done with the use of an electric coffee grinder, such as that shown in Figure 2. RICHARD NAKKA'S _EXPERIMENTAL ROCKETRY_ WEB SITE -------------------------------------------------- LATEST UPDATE: MAY 12, 2021 This website is available on a CD NEW ! Now available, Volume 11 (February 2021 creation date) Nakka-Rocketry CD is also available as a downloadable file... Click here for details... _ CD ORDERS LISTED BY COUNTRY...INTERESTING STATISTIC! _ WHAT IS THIS WEB SITE ALL ABOUT? This web site is devoted to the exciting activity of AMATEUR EXPERIMENTAL ROCKETRY ! ------------------------- MY GOAL IN PRODUCING THIS WEB SITE IS TO SHARE EXPERIENCES, IDEAS AND TECHNICAL DETAILS OF AMATEUR EXPERIMENTAL ROCKETRY WITH OTHERS AROUND THE WORLD WHO HAVE A SIMILAR INTEREST. IT IS ALSO MY DREAM TO HELP INSPIRE A FUTURE GENERATION OF ROCKET ENGINEERS AND SCIENTISTS WHO WILL SOME DAY TAKE US TO MARS AND BEYOND... ------------------------- I launched my very first amateur rocket in 1972. Since that time, so very long ago, I've built, tested and flown many rockets, powered by motors which I've developed. Over the duration of this time, I've kept detailed notes of all my work, carefully logged all the flights and other tests, and have taken countless photographs. In this web site, I am presenting at least a portion of my work. In addition to my own efforts, I am including some remarkable work done by others in pursuit of this exciting and challenging avocation. AMATEUR EXPERIMENTAL ROCKETRY ? AMATEUR EXPERIMENTAL ROCKETRY is, in my humble opinion, one of the most challenging, exciting and educational hobbies. Unlike Model Rocketry or High Power Rocketry, experimental rocketry is an activity whereby rockets are designed and constructed entirely from "scratch". Most components -- including motor and propellant-- are self-made. The goal of Amateur Experimental Rocketry (AER), often simply referred to as _Amateur Rocketry_ or _Experimental Rocketry_, is to design, build, test and launch rockets. In this context, _rocket_ may refer to the motor itself, or to a complete vehicle that consists of motor, fuselage (and stabilizing devices such as fins), nosecone, and payload. One of the greatest challenges is to develop and build such a motor, one that is safe to produce and operate, reliable, and one that provides predictable and consistent performance. A second big challenge is to develop a recovery system, such as parachute deployment, that operates with a high degree of reliability under the demanding conditions of launch followed by high speed or high altitude flight. Striving to achieve these goals (and many others) and to overcome the inevitable obstacles, is what makes this such a challenging (and at times frustrating) and educational pastime, and one that requires diversified skills combined with a good dose of ingenuity. The outcome of all this, more often than not, is that one learns to genuinely comprehend that which is colloquially known as
_Rocket Science_.
It might be said, then, that Model Rocketry and High Power Rocketry are best suited to those who wish to _make and fly rockets_, and Experimental Rocketry is perhaps best suited to those who rather wish to _make rockets fly_. ------------------------- _Contents of this web site are presented for informational purposes only_. Author of this web site cannot assume responsibility for the use readers make of the information presented herein or the devices resulting therefrom. Amateur Experimental Rocketry has many inherent hazards that must be fully understood before one can consider becoming actively involved. Safety must always be considered as top priority. Anything less is a disservice to all Amateur Experimental Rocketry enthusiasts. If you do not have first-rate common sense, or if you are willing to take shortcuts that compromise safety, then AER is not foryou.
-------------------------_ LATEST NEWS_
------------------------- November 9, 2020-- Over the past year I have been experimenting with a promising new variant of the classic Potassium Nitrate/Sorbitol (KNSB) propellant. This new propellant, which I've denoted _KNPSB_, utilizes potassium perchlorate (commonly abbreviated KP) as a supplemental oxidizer. The KP content serves to significantly boost the performance, and as an unexpected bonus, provides for easier casting thanks to a lower melt temperature and free-flowing slurry that readily pours into a casting mould. Full details are presented in my new _Potassium Nitrate/Potassium Perchlorate/Sorbitol Propellant_ web page.
July 24, 2020-- Commercial rocket altimeters utilize a _Standard Atmosphere model_ to compute altitude based on atmospheric pressure readings taken over the course of a flight. If a launch occurs when the ambient temperature is significantly different than the 15o Celsius assumed in the model, the apogee reported by the altimeter can deviate from the true apogee by several percent. My newest webpage discusses this and provides a means to make the correction. Altimeter Correction to Account for Launch Site Temperature April 30, 2020-- I decided to update the webpage on _Amateur Experimental Solid Propellants_ as I realized the information was well out-of-date. Since I originally created that webpage, several new rocket propellants suitable for use by the amateur experimentalist have evolved. I have also been made aware of formulations used with success by other experimentalists. And I have included some interesting professional formulations that may serve as inspiration to the amateur rocket engineer. ------------------------- _ QUICK ACCESS TO WEB PAGES ON THIS SITE_> GENERAL
>
> * Safety Precautions d'usage>
> * Photo Galleries of My Early Rocketry Work, Years 1972-1986>
> * Rocket Video Clips > * Who is Richard Nakka? > * How I Got Started in Rocketry _How > I Got Started in Rocketry -- PDF format)_>
> * Early Rocketry Experiments QUICK LOADING> VERSION
> * Rocketry related Technical References Jun.> 16/20
>
> * Rocketry software May 12/21 > * Links to Other Rocketry Resources Feb.18/21>
> * Sneak Preview Dec.17/20>
> * Lecture on Rocketry Presented in Luleå, Sweden>
> * The Art and Science of Rocketry Photography>
> * Lecture Notes - Presentation to University of Reykjavik, Iceland,> May 2008
> MOTORS
> * Impulser Rocket Motor ("I" Class) Nov.> 17/20
> * A-100M Rocket Motor ("G" Class) Moteur de> Fusée d'A-100M
> * B-200 Rocket Motor ("H" Class) > * C-400 Rocket Motor ("I" Class) > * A-100 Rocket Motor ("G" Class) > * Kappa Rocket Motor ("K" class) > * Juno Rocket Motor ("J" class) -- Preliminary Design>
> * Lambda Rocket Motor ("L" class) -- Preliminary Design>
> * Juno Rocket Motor -- Static Test JDX-001 Report > * Lambda Rocket Motor -- Static Test LDX-001 Report > * PVC Rocket Motors -- Introduction and Performance ("G", "H", &> "I" motors)
> * PVC Rocket Motors -- Design > * PVC Rocket Motors --Tools > * PVC Rocket Motors --Construction > * PVC Rocket Motors -- Igniters, Mounts & Conclusion>
> * PVC Rocket Motors -- Introduction & Performance ("J/K" Class> motors)
> * PVC Rocket Motors - Tools,Construction & Conclusion ("J/K" Class> motors)
> * K1000 PVC Rocket Motor > * F70 PVC Rocket Motor > * Kappa ("K" class) rocket motor -- preliminary design>
> * Kappa-DX rocket motor -- Static Test KDX-001 Report>
> * Kappa-DX rocket motor -- Static Test KDX-002 Report>
> * Kappa-SB rocket motor -- Static Test KSB-001 Report>
> * Kappa-SB rocket motor -- Static Test KSB-002 Report>
> * Epoch rocket motor ("I" Class composite) > * Paradigm rocket motor ("J" Class composite) > * Calculation of Total and Specific Impulse from Test Data>
> * Igniter Systems July 8/20 > * Nitrate-based igniters for composite propellant>
> * Case-bonding of a High-Modulus Propellant Grain > * Thermal Protection for Rocket Motor Casings > * Rocket Motor Design Charts -- Chamber Pressure > * Thermal Ablative Experimentation > * Machining of Rocket Nozzles > * Reinforcement Method for PVC Motor Casings>
>
> * Thermite Experiments> PROPELLANTS
> * Amateur Experimental Solid Propellants July> 23/20
>
> * The Potassium Nitrate/Sucrose Propellant (KNSU) > * The Potassium Nitrate/Dextrose Propellant (KNDX) > * The Potassium Nitrate/Sorbitol Propellant (KNSB) > * The Potassium Nitrate/Potassium Perchlorate/Sorbitol Propellant> (KNPSB)
> * KNSU Propellant Chemistry and Performance Characteristics>
> * KNDX Propellant Chemistry and Performance Characteristics>
> * KNSB Propellant Chemistry and Performance Characteristics>
> * The Potassium Nitrate/Epoxy Composite Propellant (RNX)>
> * Propellant Casting and Grain Preparation for the A-100M Motor>
> * INERT Propellant > * Propellant Burn Rate > * Burn Rate Determination from Static Test Pressure Measurement > Aug. 24/20 > * Strand Burner for Burn Rate Measurements > * KN-Dextrose & KN-Sorbitol Propellants -- Burn Rate> Experimentation
> * Effect of Potassium Nitrate Grade on Propellant Performance>
> * The KN-Sucrose Propellant -- A Historical Look Back>
> * Problems relating to the casting of sleeve-bonded propellant> segments
> for the Kappa-DX rocket motor Static Test KDX-001 > * Propellant Igniteability Experiment>
> * Propellant Inhibitor Experiment>
> * Experiments with Potassium Nitrate - Epoxy Formulations>
>
> * Burn Characteristics of Sorbitol Based Propellants>
>
> * Experiments with Oxides and other possible Burn Rate Modifiers>
>
> * Synthesis of Potassium Nitrate from Other Chemicals > Sep. 16/20 > * Purification of Low-grade Potassium Nitrate>
> * Experiments with Ammonium Nitrate / Aluminum based Propellant > Formulations _Spanish translation_>
>
> * Development of a Metalized Ammonium Nitrate-based Propellant>
>
> * Harvesting Aluminum Powder from Paint> TESTING
> * Rocket Motor Static Testing May 14/20 > * Measuring Chamber Pressure and Determining C-Star and Thrust > Coefficient May 26/20 > * STS-5000 Static Test Stand May 25/20 > * Hydraulic Load Cell for Thrust measurement > * Strain Gage Load Cell for Thrust measurement > * Mounting Strain Gages on a Loadcell > * Strain Gages available to purchase > * Pressure Transformer> ROCKETS
> * _Xi_ Series of Rocket Flights Apr. 15/21>
> * _Zeta_ Series of Rocket Flights>
> * _DS_ Series of Rocket Flights>
> * Launch Report -_Frostfire 3_ Rocket > * Launch Report -_SkyDart_ Rocket, Flight SD-1 > * Launch Report -_SkyDart_ Rocket, Flight SD-2 > * Launch Report -_SkyDart_ Rocket, Flight SD-3 > * Launch Report -_Frostfire Two _Rocket > * Launch Report -_Zephyr _Rocket, Flight _Ze-1_ > * Launch Report -_Zephyr _Rocket, Flight _Ze-2_ > * Launch Report -_Zephyr _Rocket, Flight _Ze-3_ > * _Boreas 1_ Rocket > * Launch Report -- _Epoch _Rocket Motor (unofficial) Inaugural> Flight
> * Launch Report - _Boreas 1_ Inaugural Flight > * Launch Report - _Boreas 1_, Flight #2 > * Launch Report - _Boreas 1_, Flight #3 > * Launch Report -_ Boreas 1_, Flight #4 > * Launch Report - _Boreas 1_, Flight #5 > * Launch Report -_ Frostfire One_ > * Cirrus Project > * _Cirrus One_ Launch Report > * _Cirrus TV-1_ Launch Report > * Launch Report - Chuck Knight's _Photo1_ Rocket > * Rocket Construction > * Fins for Rocket Stability > * Construction of a Rocket Body using sheet aluminum>
> * Rocket Body Structural Strength > * Launch Support System > * Launch Controller Circuit>
> * Radio Transmitter>
> * EMT Tripod Rocket Launcher>
> * Simplified Method for Estimating the Flight Performance of a> Rocket
> * Smoke Tracking>
> * Altimeter Correction to Account for Launch Site Temperature>
>
> * Launch Wagon Description> RECOVERY SYSTEM
> * DS Rocket Recovery System Description>
> * Rocket Parachute Ejection System -- _Zephyr_, _Boreas _and > _Frostfire _series (schematic) > * Rocket Recovery System Timer > * Air-Speed Triggering System for Parachute Deployment>
> * Rocket Altimeter System > * Parachute Design and Construction Mar. 6/20>
> * Parts List (parachute construction) > * Parachute Structural and Drag Testing > * Cross Parachute Construction > * Construction of a _ 1 metre_ Cross Parachute>
> * Crimson Powder for Parachute Ejection Charge>
>
> * Pyrogen - Delay Ejection Device (Pyro-DED)>
> THEORY
> * Introduction to _Solid Rocket Motor_ Theory > * Basic Assumptions > * Propellant Grain > * Propellant Combustion > * Nozzle Theory > * Motor Thrust > * Motor Impulse > * Chamber Pressure > * Two-Phase Flow > * Corrections for Actual Rocket Motors > * GUIPEP Propellant Performance Software > * Theory Appendices > * Solid Rocket Motor Theory webpages in PDF format>
> * Teoría Sobre Motores Cohete De propelente Sólido > (Spanish Translation)>
> * Teoria de motor-foguete sólido> (Portugese
> Translation)
> * Théorie des moteurs de fusée à propulseur solide > (French Translation) > * Fundamentos de propulsão sólida de foguetes > (Portugese) 10 Mbyte > * Derivation of Selected Rocket Equations>
> MISCELLANEOUS
> * Numerical Simulation of the Under-expanded Flow in the > Experimental Conical Nozzle Helios-X>
> * Simulación Numérica del Flujo Sub-expandido en la Tobera > Cónica Experimental Helios-X>
>
> * Construction of a Balance Scale for precision weighing>
> * Experimental Reports > * Technical Notepad #1 -- KNSU Ideal Performance Calculations>
> * Technical Notepad #2 -- KNDX Ideal Performance Calculations>
> * Technical Notepad #3 -- KNSB Ideal Performance Calculations>
> * Technical Notepad #4 - Convective Heat Transfer Coefficient> Calculation
> * Technical Notepad #5 -- KNER Ideal Performance Calculations>
> * Technical Notepad #6 -- A24 Ideal Performance Calculations>
> * Technical Notepad #7 -- RNX-71V Ideal Performance Calculations>
> * Technical Notepad #8 -- RNX-57 Ideal Performance Calculations>
> * Technical Notepad #9 -- KNPSB Ideal Performance Calculations> Feb.10/21
> * Technical Notepad #10 -- KNXY Ideal Performance Calculations>
> * Downloads > * Spanish translation of several articles featured on my website>
> * Arabic translation of _Solid Propellant Rocket Motor Design and> Testing_ by
> R.Nakka (translation by Mohamed Elaouni)(PDF format) > * Links to over 100 NASA Space Vehicle Design (SP8000) Reports> Mar.29/21
> * Links to Selected STINET Reports > * Moonwalk Audio Recording and TV Screen Photos>
> ------------------------->
> If you have any questions or comments > feel free to send me e-mail>
> Include the word "rocketry" in the subject line to ensure your > e-mail gets past my spam filter>
> ------------------------->
> Reports of broken links or viewing, graphics, & downloading problems > are much appreciated !>
> ------------------------->
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> Web > nakka-rocketry.net>
> THIS SITE ORIGINALLY POSTED JULY 1997>
> ------------------------- > _"A man's reach should exceed his grasp...else, what's the heavens> for?"_
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