Add to ORKGPlotted and tabulated data on heat transfer from a thin-skin thermocouple are presented. The data is representative of the reentry event of the booster alone configuration. The data were generated during wind tunnel tests of the B-15B-2 delta wing booster at Mach 8. Thermocouple measurements are reduced to heat transfer coefficient ratio and the data are presented as plotted variations versus longitudinal, lateral, and vertical local model positions
Results from wind tunnel tests to determine hypersonic aerodynamic heating rates on a NASA/Rockwell ...
Hypervelocity wind tunnel tests of Convair B8B space shuttle booster and model configuration perturb...
Results are presented of heat transfer tests of a 147B configuration orbiter model (50-0) conducted ...
Plots and tables which determine detailed heat transfer distributions on phase B space shuttle confi...
The tests were conducted in a hypersonic wind tunnel at Mach number 8 to investigate reentry mode co...
A wind tunnel test program to determine aerodynamic interference heating on the North American Rockw...
The results are presented of a wind tunnel test program to determine aerodynamic heat transfer distr...
Results of wind tunnel heat transfer tests of 0.0175-scale Rockwell International Space Shuttle Vehi...
Results of wind tunnel heat transfer tests of 0.0175-scale Rockwell International Space Shuttle Vehi...
A wind tunnel test program to determine aerodynamic heat transfer distributions on the McDonnell-Dou...
Aerothermodynamic tests of Phase B space shuttle configurations proposed by North American Rockwell/...
Aerothermodynamic tests on the forward half of the Rockwell International Space Shuttle Orbiter Conf...
Ascent heating data were obtained at conditions simulating real gas effects at hypersonic Mach numbe...
Design of an efficient thermal protection system for the space shuttle orbiter and booster is discus...
The results of a wind tunnel test program to determine aerodynamic heat transfer distributions on an...
Results from wind tunnel tests to determine hypersonic aerodynamic heating rates on a NASA/Rockwell ...
Hypervelocity wind tunnel tests of Convair B8B space shuttle booster and model configuration perturb...
Results are presented of heat transfer tests of a 147B configuration orbiter model (50-0) conducted ...
Plots and tables which determine detailed heat transfer distributions on phase B space shuttle confi...
The tests were conducted in a hypersonic wind tunnel at Mach number 8 to investigate reentry mode co...
A wind tunnel test program to determine aerodynamic interference heating on the North American Rockw...
The results are presented of a wind tunnel test program to determine aerodynamic heat transfer distr...
Results of wind tunnel heat transfer tests of 0.0175-scale Rockwell International Space Shuttle Vehi...
Results of wind tunnel heat transfer tests of 0.0175-scale Rockwell International Space Shuttle Vehi...
A wind tunnel test program to determine aerodynamic heat transfer distributions on the McDonnell-Dou...
Aerothermodynamic tests of Phase B space shuttle configurations proposed by North American Rockwell/...
Aerothermodynamic tests on the forward half of the Rockwell International Space Shuttle Orbiter Conf...
Ascent heating data were obtained at conditions simulating real gas effects at hypersonic Mach numbe...
Design of an efficient thermal protection system for the space shuttle orbiter and booster is discus...
The results of a wind tunnel test program to determine aerodynamic heat transfer distributions on an...
Results from wind tunnel tests to determine hypersonic aerodynamic heating rates on a NASA/Rockwell ...
Hypervelocity wind tunnel tests of Convair B8B space shuttle booster and model configuration perturb...
Results are presented of heat transfer tests of a 147B configuration orbiter model (50-0) conducted ...