NASA has recently developed and proof tested a pilot cryogenic transonic pressure tunnel. In addition to providing an attractive method for obtaining high Reynolds number results at moderate aerodynamic loadings and tunnel power, this unique facility enables the independent determination of the effects of Reynolds number, Mach number, and aeroelasticity. The proof-of-concept experimental and theoretical studies are briefly reviewed. Experimental results are included which indicate pressure distributions for a two-dimensional airfoil and strain-gage balance characteristics for a three-dimensional delta wing model.
Test results from the Langley high Reynolds number cryogenic transonic tunnel
Aerodynamic Testing Conference ; 1974 ; Bethesda, MD
01.07.1974
Aufsatz (Konferenz)
Keine Angabe
Englisch