The Cryogenic Wind-tunnel Concept for High Reynolds Number Testing
Author :
Publisher :
Page : 100 pages
File Size : 45,22 MB
Release : 1974
Category : Low temperature engineering
ISBN :
Author :
Publisher :
Page : 100 pages
File Size : 45,22 MB
Release : 1974
Category : Low temperature engineering
ISBN :
Author :
Publisher :
Page : 100 pages
File Size : 22,43 MB
Release : 1986
Category :
ISBN :
Author : Marie H. Tuttle
Publisher :
Page : 146 pages
File Size : 11,74 MB
Release : 1991
Category : Low temperature engineering
ISBN :
Author :
Publisher :
Page : 18 pages
File Size : 32,16 MB
Release : 1985
Category :
ISBN :
Author : Robert Ashworth Kilgore
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Page : pages
File Size : 35,27 MB
Release : 1974
Category :
ISBN :
Author : Marie H. Tuttle
Publisher :
Page : 116 pages
File Size : 37,59 MB
Release : 1985
Category : Low temperature engineering
ISBN :
Author :
Publisher :
Page : 26 pages
File Size : 25,53 MB
Release : 1976
Category :
ISBN :
Author : Marie H. Tuttle
Publisher :
Page : 36 pages
File Size : 30,27 MB
Release : 1979
Category : Low temperature engineering
ISBN :
Author :
Publisher :
Page : 62 pages
File Size : 30,10 MB
Release : 1979
Category :
ISBN :
Author : Robert A. Kilgore
Publisher :
Page : 28 pages
File Size : 27,27 MB
Release : 1974
Category : Low temperature engineering
ISBN :
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 are 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 were examined and found to be insignificant for operating pressures up to 5 atm. The characteristics of the Langley pilot transonic cryogenic 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 atm at a stagnation temperature of 322.0 K and then at a stagnation pressure of 1.19 atm at a stagnation temperature of 116.5 K.