Add to ORKGThe results of a wind tunnel test to determine the force, moment, and hinge-moment characteristics of the Configuration 2A Space Shuttle Vehicle Orbiter at Mach numbers 5, 7 and 10 are presented. The model was an 0.015-scale representation of the Orbiter Configuration 2A used in test 0A11A and later tests. Six-component aerodynamic force and moment data were recorded from a 1.50-inch internal strain-gage balance, and base pressures were taken for axial and drag force corrections. Hinge-moment data were obtained for the rudder and the inboard and outboard elevon panels of the starboard wing
The results of wind tunnel tests conducted on a 0.010-scale version of the Vehicle 3 Space Shuttle C...
A wind tunnel test was conducted of an 0.030 scale model of the space shuttle orbiter in a supersoni...
Tests were conducted to obtain hypersonic aerodynamic forces and moments on an 0.010-scale model of ...
Experimental aerodynamic investigations were conducted in the NASA/Ames 3.5-Foot Hypersonic wind Tun...
Longitudinal and lateral-directional stability and control characteristics were evaluated at Mach nu...
The primary objective of the test was to obtain stability and control data for the basic configurati...
Experimental aerodynamic investigations were conducted on a scale model of the space shuttle orbiter...
A wind tunnel test of an 0.030-scale space shuttle vehicle orbiter configuration 140A/B model was co...
Wind tunnel tests were conducted of the NASA/Rockwell 0.015 scale configuration 4 mated space shuttl...
The results of a wind tunnel test are presented; the model used for this test was 0.015-scale 140 A/...
Experimental investigations were performed in a 6- by 6-Foot Supersonic wind tunnel on a 0.015-scale...
Experimental aerodynamic investigations were conducted in the NASA/Ames Research Center 3.5-foot hyp...
Tests were conducted in the NASA/ARC Unitary Plan wind tunnels on an 0.030-scale replica of the spac...
Experimental aerodynamic investigations were conducted in NASA/Langley 8-Foot transonic pressure tun...
Experimental aerodynamic investigations were conducted in the NASA Ames Research Center 3.5-Foot Hyp...
The results of wind tunnel tests conducted on a 0.010-scale version of the Vehicle 3 Space Shuttle C...
A wind tunnel test was conducted of an 0.030 scale model of the space shuttle orbiter in a supersoni...
Tests were conducted to obtain hypersonic aerodynamic forces and moments on an 0.010-scale model of ...
Experimental aerodynamic investigations were conducted in the NASA/Ames 3.5-Foot Hypersonic wind Tun...
Longitudinal and lateral-directional stability and control characteristics were evaluated at Mach nu...
The primary objective of the test was to obtain stability and control data for the basic configurati...
Experimental aerodynamic investigations were conducted on a scale model of the space shuttle orbiter...
A wind tunnel test of an 0.030-scale space shuttle vehicle orbiter configuration 140A/B model was co...
Wind tunnel tests were conducted of the NASA/Rockwell 0.015 scale configuration 4 mated space shuttl...
The results of a wind tunnel test are presented; the model used for this test was 0.015-scale 140 A/...
Experimental investigations were performed in a 6- by 6-Foot Supersonic wind tunnel on a 0.015-scale...
Experimental aerodynamic investigations were conducted in the NASA/Ames Research Center 3.5-foot hyp...
Tests were conducted in the NASA/ARC Unitary Plan wind tunnels on an 0.030-scale replica of the spac...
Experimental aerodynamic investigations were conducted in NASA/Langley 8-Foot transonic pressure tun...
Experimental aerodynamic investigations were conducted in the NASA Ames Research Center 3.5-Foot Hyp...
The results of wind tunnel tests conducted on a 0.010-scale version of the Vehicle 3 Space Shuttle C...
A wind tunnel test was conducted of an 0.030 scale model of the space shuttle orbiter in a supersoni...
Tests were conducted to obtain hypersonic aerodynamic forces and moments on an 0.010-scale model of ...