Add to ORKGTests were conducted in wind tunnels during April and May 1973, on a 0.030-scale replica of the Space Shuttle Vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests on the integrated (launch) configuration and the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from -8 degrees to +8 degrees. The isolated orbiter was tested at angles of attack from -15 degrees to +40 degrees and angles of sideslip from -10 degrees to +10 degrees as dictated by trajectory considerations. The effects of orbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were also investigated. Tabulated pres...
The purpose of the test was to determine the effects of cold jet gas plumes on (1) the integrated ve...
Experimental aerodynamic investigations were conducted in NASA/Langley 8-Foot transonic pressure tun...
Tests were conducted in the NASA/ARC 6- by 6-foot transonic wind tunnel from September 12 to Septemb...
Tests were conducted in wind tunnels during April and May 1973, on a 0.030-scale replica of the Spac...
Tests were conducted in the NASA/ARC Unitary Plan wind tunnels on an 0.030-scale replica of the spac...
Tests were conducted in wind tunnels during April and May 1973, on an 0.030-scale replica of the Spa...
Tests were conducted in the NASA/ARC Unitary Plan Wind Tunnels on an 0.030 scale replica of the spac...
Tests were conducted in wind tunnels during April and May 1973, on an 0.030-scale replica of the Spa...
Tests were conducted in unitary plan wind tunnels on an 0.030-scale replica of the space shuttle veh...
The results of the tests are presented along with aerodynamic loads data obtained at Mach numbers fr...
Longitudinal and lateral-directional stability and control characteristics were evaluated at Mach nu...
Experimental aerodynamic investigations were conducted in the NASA/Ames Research Center 3.5-foot hyp...
The investigations of pressure distributions are presented for aeroloads analysis at Mach numbers fr...
Pressure data are presented in tabular form on the left and right vertical tail surface of the space...
The purpose of the test was to determine the effects of cold jet gas plumes on (1) the integrated ve...
The purpose of the test was to determine the effects of cold jet gas plumes on (1) the integrated ve...
Experimental aerodynamic investigations were conducted in NASA/Langley 8-Foot transonic pressure tun...
Tests were conducted in the NASA/ARC 6- by 6-foot transonic wind tunnel from September 12 to Septemb...
Tests were conducted in wind tunnels during April and May 1973, on a 0.030-scale replica of the Spac...
Tests were conducted in the NASA/ARC Unitary Plan wind tunnels on an 0.030-scale replica of the spac...
Tests were conducted in wind tunnels during April and May 1973, on an 0.030-scale replica of the Spa...
Tests were conducted in the NASA/ARC Unitary Plan Wind Tunnels on an 0.030 scale replica of the spac...
Tests were conducted in wind tunnels during April and May 1973, on an 0.030-scale replica of the Spa...
Tests were conducted in unitary plan wind tunnels on an 0.030-scale replica of the space shuttle veh...
The results of the tests are presented along with aerodynamic loads data obtained at Mach numbers fr...
Longitudinal and lateral-directional stability and control characteristics were evaluated at Mach nu...
Experimental aerodynamic investigations were conducted in the NASA/Ames Research Center 3.5-foot hyp...
The investigations of pressure distributions are presented for aeroloads analysis at Mach numbers fr...
Pressure data are presented in tabular form on the left and right vertical tail surface of the space...
The purpose of the test was to determine the effects of cold jet gas plumes on (1) the integrated ve...
The purpose of the test was to determine the effects of cold jet gas plumes on (1) the integrated ve...
Experimental aerodynamic investigations were conducted in NASA/Langley 8-Foot transonic pressure tun...
Tests were conducted in the NASA/ARC 6- by 6-foot transonic wind tunnel from September 12 to Septemb...