Add to ORKGStatic pressure distributions for the external tank (ET) at reentry conditions are presented. Basic configuration of the model was the MCR 0200 ET modified to include a rectangular crossbar at the aft ET/orbiter attach point. Mach numbers were 1.96, 3.48, and 4.96. Reynolds number per foot at these Mach numbers were 6.95 million, 6.42 million, and 4.95 million, respectively. Angle of attack range was -8 to 100 degrees and roll angle was 0 to 315 degrees
Data were obtained on a 3-percent model of the Space Shuttle launch vehicle in the NASA/Ames Researc...
Pressure data are presented in tabular form on the external tank base and SRM booster base of the sp...
Pressure data are presented in tabular form on the left and right vertical tail surface of the space...
Data were obtained for Mach numbers from 0.6 to 3.48, angles of attack from -10 to 10 degrees, and a...
The results of a pressure test of a .00548 scale 146 inch Space Shuttle Solid Rocket Booster (SRB) w...
Tests were conducted, from November 15 to December 4, 1973, to obtain surface pressure data on an 0....
Results of wind tunnel tests, conducted at the Langley Research Center Unitary Plan Wind Tunnel, are...
Pressure data are presented in tabular form on the external tank attach points and the external tank...
Experimental aerodynamic investigations were conducted during mid-July, 1973 on a .004 scale model o...
Pressure data are presented in tabular form on the external tank and the SRM nozzle of the space shu...
Test results are presented of hypersonic pressure distributions at simulated atmospheric entry condi...
The results of the tests are presented along with aerodynamic loads data obtained at Mach numbers fr...
The model tested was a 0.0091 scale representation of the ogive nose section of the External Tank wi...
An experimental Aerodynamic and Aero-Acoustic loads data base was obtained at transonic Mach numbers...
The investigations of pressure distributions are presented for aeroloads analysis at Mach numbers fr...
Data were obtained on a 3-percent model of the Space Shuttle launch vehicle in the NASA/Ames Researc...
Pressure data are presented in tabular form on the external tank base and SRM booster base of the sp...
Pressure data are presented in tabular form on the left and right vertical tail surface of the space...
Data were obtained for Mach numbers from 0.6 to 3.48, angles of attack from -10 to 10 degrees, and a...
The results of a pressure test of a .00548 scale 146 inch Space Shuttle Solid Rocket Booster (SRB) w...
Tests were conducted, from November 15 to December 4, 1973, to obtain surface pressure data on an 0....
Results of wind tunnel tests, conducted at the Langley Research Center Unitary Plan Wind Tunnel, are...
Pressure data are presented in tabular form on the external tank attach points and the external tank...
Experimental aerodynamic investigations were conducted during mid-July, 1973 on a .004 scale model o...
Pressure data are presented in tabular form on the external tank and the SRM nozzle of the space shu...
Test results are presented of hypersonic pressure distributions at simulated atmospheric entry condi...
The results of the tests are presented along with aerodynamic loads data obtained at Mach numbers fr...
The model tested was a 0.0091 scale representation of the ogive nose section of the External Tank wi...
An experimental Aerodynamic and Aero-Acoustic loads data base was obtained at transonic Mach numbers...
The investigations of pressure distributions are presented for aeroloads analysis at Mach numbers fr...
Data were obtained on a 3-percent model of the Space Shuttle launch vehicle in the NASA/Ames Researc...
Pressure data are presented in tabular form on the external tank base and SRM booster base of the sp...
Pressure data are presented in tabular form on the left and right vertical tail surface of the space...