Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722219987
Category :
Languages : en
Pages : 24
Book Description
An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at combustion chamber pressures of 12.4 to 16.5 MPa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse. Jankovsky, Robert S. and Kazaroff, John M. and Pavli, Albert J. Glenn Research Center NAS3-27186; RTOP 506-42-72...
Experimental Performance of a High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722219987
Category :
Languages : en
Pages : 24
Book Description
An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at combustion chamber pressures of 12.4 to 16.5 MPa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse. Jankovsky, Robert S. and Kazaroff, John M. and Pavli, Albert J. Glenn Research Center NAS3-27186; RTOP 506-42-72...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722219987
Category :
Languages : en
Pages : 24
Book Description
An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at combustion chamber pressures of 12.4 to 16.5 MPa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse. Jankovsky, Robert S. and Kazaroff, John M. and Pavli, Albert J. Glenn Research Center NAS3-27186; RTOP 506-42-72...
Experimental Performance of a High-area-ratio Rocket Nozzle at High Combustion Chamber Pressure
Author: Robert S. Jankovsky
Publisher:
ISBN:
Category : Combustion chambers
Languages : en
Pages : 28
Book Description
An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at combustion chamber pressures of 12.4 to 16.5 MPa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse.
Publisher:
ISBN:
Category : Combustion chambers
Languages : en
Pages : 28
Book Description
An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at combustion chamber pressures of 12.4 to 16.5 MPa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse.
High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure: Experimental and Analytical Validation
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723849435
Category : Science
Languages : en
Pages : 58
Book Description
Experimental data were obtained on an optimally contoured nozzle with an area ratio of 1025:1 and on a truncated version of this nozzle with an area ratio of 440:1. The nozzles were tested with gaseous hydrogen and liquid oxygen propellants at combustion chamber pressures of 1800 to 2400 psia and mixture ratios of 3.89 to 6.15. This report compares the experimental performance, heat transfer, and boundary layer total pressure measurements with theoretical predictions of the current Joint Army, Navy, NASA, Air Force (JANNAF) developed methodology. This methodology makes use of the Two-Dimensional Kinetics (TDK) nozzle performance code. Comparisons of the TDK-predicted performance to experimentally attained thrust performance indicated that both the vacuum thrust coefficient and the vacuum specific impulse values were approximately 2.0-percent higher than the turbulent prediction for the 1025:1 configurations, and approximately 0.25-percent higher than the turbulent prediction for the 440:1 configuration. Nozzle wall temperatures were measured on the outside of a thin-walled heat sink nozzle during the test fittings. Nozzle heat fluxes were calculated front the time histories of these temperatures and compared with predictions made with the TDK code. The heat flux values were overpredicted for all cases. The results range from nearly 100 percent at an area ratio of 50 to only approximately 3 percent at an area ratio of 975. Values of the integral of the heat flux as a function of nozzle surface area were also calculated. Comparisons of the experiment with analyses of the heat flux and the heat rate per axial length also show that the experimental values were lower than the predicted value. Three boundary layer rakes mounted on the nozzle exit were used for boundary layer measurements. This arrangement allowed total pressure measurements to be obtained at 14 different distances from the nozzle wall. A comparison of boundary layer total pressure profiles and analytical
Publisher: Independently Published
ISBN: 9781723849435
Category : Science
Languages : en
Pages : 58
Book Description
Experimental data were obtained on an optimally contoured nozzle with an area ratio of 1025:1 and on a truncated version of this nozzle with an area ratio of 440:1. The nozzles were tested with gaseous hydrogen and liquid oxygen propellants at combustion chamber pressures of 1800 to 2400 psia and mixture ratios of 3.89 to 6.15. This report compares the experimental performance, heat transfer, and boundary layer total pressure measurements with theoretical predictions of the current Joint Army, Navy, NASA, Air Force (JANNAF) developed methodology. This methodology makes use of the Two-Dimensional Kinetics (TDK) nozzle performance code. Comparisons of the TDK-predicted performance to experimentally attained thrust performance indicated that both the vacuum thrust coefficient and the vacuum specific impulse values were approximately 2.0-percent higher than the turbulent prediction for the 1025:1 configurations, and approximately 0.25-percent higher than the turbulent prediction for the 440:1 configuration. Nozzle wall temperatures were measured on the outside of a thin-walled heat sink nozzle during the test fittings. Nozzle heat fluxes were calculated front the time histories of these temperatures and compared with predictions made with the TDK code. The heat flux values were overpredicted for all cases. The results range from nearly 100 percent at an area ratio of 50 to only approximately 3 percent at an area ratio of 975. Values of the integral of the heat flux as a function of nozzle surface area were also calculated. Comparisons of the experiment with analyses of the heat flux and the heat rate per axial length also show that the experimental values were lower than the predicted value. Three boundary layer rakes mounted on the nozzle exit were used for boundary layer measurements. This arrangement allowed total pressure measurements to be obtained at 14 different distances from the nozzle wall. A comparison of boundary layer total pressure profiles and analytical
Experimental Thrust Performance of a High-area-ratio Rocket Nozzle
Author: Albert J. Pavli
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 20
Book Description
Experimental Performance of Area Ratio 200, 25 and 8 Nozzles on JP-4 Fuel and Liquid Oxygen Rocket Engine
Author: Calvin J. Lovell
Publisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 22
Book Description
Publisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 22
Book Description
Comparison of Theoretical and Experimental Thrust Performance of a 1030:1 Area Ratio Rocket Nozzle at a Chamber Pressure of 2413 KN/m2 (350 Psia)
Author: Tamara A. Smith
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 28
Book Description
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 28
Book Description
Experimental Performance of a Hydrogen-fluorine Rocket Engine at Several Chamber Pressures and Exhaust-nozzle Expansion Area Ratios
Author: William L. Jones
Publisher:
ISBN:
Category : Boron as fuel
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Boron as fuel
Languages : en
Pages : 38
Book Description
High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure: Experimental and Analytical Validation
Author: Robert S. Jankovsky
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 60
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 60
Book Description
Experimental Rocket Performance of Apollo Storable Propellants in Engines with Large Area Ratio Nozzles
Author: Carl A. Aukerman
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 52
Book Description
Experimental Evaluation of Heat Transfer on a 1030:1 Area Ratio Rocket Nozzle
Author: Kenneth J. Kacynski
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 32
Book Description