HIGH REYNOLDS NUMBER TESTS OF A C-141A AIRCRAFT SEMISPAN MODEL TO INVESTIGATE SHOCK-INDUCED SEPARATION

摘要

Results from a high Reynolds number transonic wind tunnel investigation on a semispan model of the C-141A airplane are presented. Wing chordwise pressure distributions were measured over a matrix of Mach numbers and angles-of-attack for which shock-induced separations are known to exist. The range of Reynolds number covered by these data nearly spanned the gap between previously available wind tunnel and flight test data. The results are compared with both flight and low Reynolds number data.