Efforts to develop a near sonic transport have placed renewed emphasis on obtaining accurate aerodynamic force and pressure data in the near sonic speed range. Comparison of wind-tunnel and flight data obtained for a blunt-nose body of revolution showed significant discrepancies in drag levels near Mach 1 - apparently due to wind-tunnel wall interference. Subsequent tests of geometrically similar bodies of revolution showed that increasing the model-to-test-section blockage ratio from 0.00017 to 0.0043 resulted in altered drag curve shapes, delayed drag divergence, and 'transonic creep' from subsonic drag levels due to increased wall interference.
Transonic wall interference effects on bodies of revolution.
American Institute of Aeronautics and Astronautics, Aerodynamic Testing Conference
01.09.1972
Aufsatz (Konferenz)
Keine Angabe
Englisch
Calculation of transonic wall interference
AIAA | 1987
|Transonic wind tunnel wall interference minimization
AIAA | 1984
|