The characteristics of the Langley 34 cm (13.5 in.) pilot cryogenic transonic pressure tunnel are described, and the results of initial tunnel operation are presented. Tests of a two-dimensional airfoil at a Mach number of 0.85 show identical pressure distributions for a chord Reynolds number of 8,600,000 obtained first at a stagnation pressure of 4.91 atmospheres at a stagnation temperature of +120 F and then at a stagnation pressure of 1.19 atmospheres at a stagnation temperature of -250 F.
Flight simulation characteristics of the Langley high Reynolds number cryogenic transonic tunnel
Aerospace Sciences Meeting ; 1974 ; Washington, DC
1974-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch