The methodology involved in developing the ability to reproduce aerodynamic results between various wind tunnel tests and to determine uncertainties due to differences between preflight aerodynamic predictions and flight results derived from analysis of past aircraft programs is presented. The uncertainties were developed for pitching moment, lateral-directional stability, rudder power, and aileron power, and were formulated to yield aerodynamic uncertainties for an orbital, manned first flight. The compressed development schedule required the aerodynamics results from wind tunnel tests be equipped with tolerances, which accounted for reasonable changes in the vehicle configuration. A worst case scenario was decided on, with the results that every prediction included the widest possible aerodynamic margins. Repeatibility was emphasized between wind tunnel model tests, and was achieved with an accuracy of 0.006 with inclusion of Reynolds effects.
The development of aerodynamic uncertainties for the Space Shuttle Orbiter
In: Aerodynamic Testing Conference ; 1982 ; Williamsburg, VA
1982-01-01
Miscellaneous
No indication
English
Space Shuttle orbiter aerodynamic development
AIAA | 1974
|Space Shuttle Orbiter Aerodynamic Development
AIAA | 1978
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