Gamma-effects on 2-dimensional transonic aerodynamicsNonlifting 10% biconvex airfoils are mounted in a 30 x 40 cm Ludwieg-tube-driven transonic test-section and the flow field recorded with a holographic interferometer. Nitrogen, argon, and carbon dioxide are used as the principal test gases. Experiments are conducted with Reynolds number based on chord of (0.5-3.5) x 10 to the 6th with Mach numbers of 0.70, 0.75, and 0.80. Supporting calculations use inviscid transonic small-disturbance and full-potential computer codes coupled with simple integral boundary-layer modeling. Systematic studies show that significant gamma-effects can occur due to shock-induced separation.
Document ID
19760055666
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Tuzla, K. (Washington Univ. Seattle, WA, United States)
Russell, D. A. (Washington, University Seattle, Wash., United States)
Wai, J. C. (Washington Univ. Seattle, WA, United States)