Author :
Publisher :
Page : 110 pages
File Size : 14,98 MB
Release : 1972
Category :
ISBN :
Author :
Publisher :
Page : 704 pages
File Size : 15,67 MB
Release : 1995
Category : Aeronautics
ISBN :
Author : J. Schneider
Publisher :
Page : 106 pages
File Size : 40,99 MB
Release : 1972
Category : Boundary layer
ISBN :
A computer program is described capable of determining the properties of a compressible turbulent boundary layer with pressure gradient and heat transfer. The program treats the two-dimensional problem assuming perfect gas and Crocco integral energy solution. A compressibility transformation is applied to the equation for the conservation of mass and momentum, which relates this flow to a low speed constant property flow with simultaneous mass transfer and pressure gradient. The resulting system of describing equations consists of eight ordinary differential equations which are solved numerically. For Part 1, see N72-12226; for Part 2, see N72-15264.
Author :
Publisher :
Page : 1388 pages
File Size : 19,44 MB
Release :
Category : Government publications
ISBN :
Author : United States. Superintendent of Documents
Publisher :
Page : 1408 pages
File Size : 12,5 MB
Release : 1976
Category : United States
ISBN :
Author :
Publisher :
Page : 978 pages
File Size : 40,29 MB
Release : 1972
Category : Government publications
ISBN :
Author :
Publisher :
Page : 100 pages
File Size : 45,58 MB
Release : 1970
Category :
ISBN :
Author : C. Economos
Publisher :
Page : 92 pages
File Size : 18,22 MB
Release : 1972
Category : Transformations (Mathematics)
ISBN :
A generalized form of the Coles compressibility transformation is utilized to analyze compressible turbulent boundary-layer flows. The generalization in the transformation is distinguished by specifying a stretching parameter that depends upon both space variables rather than on only the streamwise coordinate. This modification is shown to eliminate the distortion observed in the wake region of the transformed velocity profiles. For zero pressure gradient flows, predictions based upon the analysis are consistently superior with predictions due to Spalding-Chi and Baronti-Libby. A wide range of experimental data have been examined with Mach numbers ranging as high as 8, wall to free stream total temperature ratios as low as 0.25 and momentum thickness Reynolds numbers up to approximately one million.
Author :
Publisher :
Page : 530 pages
File Size : 25,94 MB
Release : 1971
Category : Computer programming
ISBN :
Author :
Publisher :
Page : 1092 pages
File Size : 38,54 MB
Release : 1973
Category : Aerodynamic load
ISBN :
The results of the Task 1 and 2 turbine design work are reported. Preliminary design is discussed. Blading detailed design data are summarized. Predicted performance maps are presented. Steady-state stresses and vibratory behavior are discussed, and the results of the mechanical design analysis are presented. -- [V]. I The experimental test program results of a 4 1/2-stage turbine with a very high stage loading factor are presented. A four-stage turbine was tested with and without outlet turning vanes. The 4 1/2-stage turbine achieved a design point total-to-total efficiency of 0.853. The outlet turning vane design point performance was 0.4 percent of the overall 4 1/2-stage turbine efficiency. Tests were conducted at various levels of Reynolds number and indicated decreases in turbine efficiency and equivalent weight flow with decreasing Reynolds number. --[V]. II.
