The theory and advantages of the cryogenic tunnel concept are briefly reviewed. The unique ability to vary temperature independently of pressure and Mach number allows, in addition to large reductions in model loads and tunnel power, the independent determination of Reynolds number, Mach number, and aeroelastic effects on the aerodynamic characteristics of the model. Various combinations of Reynolds number and dynamic pressure can be established to represent accurately flight variations of aeroelastic deformation with altitude changes. The consequences of the thermal and caloric imperfections of the test gas under cryogenic conditions have been found insignificant for operating pressures up to 5 atm. 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.
Flight simulation characteristics of the Langley high Reynolds number cryogenic transonic tunnel
Flugsimulationscharakteristiken von der Langley-<sup>Reynold'sche</sup>Zahl kaelteerzeugender Ueberschalltunnel
Journal of Aircraft ; 11 , 10 ; 593-600
1974
, 4 Quellen
Article (Journal)
English