Author : Louis S. Stivers
Publisher :
Page : 32 pages
File Size : 48,27 MB
Release : 1960
Category : Airplanes
ISBN :
Author :
Publisher :
Page : 38 pages
File Size : 11,78 MB
Release : 1960
Category :
ISBN :
Author : Louis S. Stivers
Publisher :
Page : 28 pages
File Size : 40,99 MB
Release : 1960
Category :
ISBN :
Author :
Publisher :
Page : 1206 pages
File Size : 29,39 MB
Release : 1967
Category : Aeronautics
ISBN :
Author : United States. National Aeronautics and Space Administration
Publisher :
Page : pages
File Size : 29,11 MB
Release : 1960-07
Category :
ISBN :
Author : S. R. Pate
Publisher :
Page : 58 pages
File Size : 45,47 MB
Release : 1963
Category : Boundary layer
ISBN :
Tests were conducted in the 12-in. Supersonic Tunnel of the von Karman Gas Dynamics Facility to determine boundary-layer transition locations on swept wings having a circular arc profile and modified arc profile. Test Mach numbers were from 2.5 to 5 over a Reynolds-number-per-inch range from 0.14 to 1. 08 million at sweep angles of 24, 36, and 50 deg for angles of attack of 0 and approximately -4 deg. Boundary-layer transition Reynolds numbers determined by a pitot probe, and results obtained visually with a sub limable solid are presented. The major factors influencing boundary-layer transition were wing sweep and model leading edge geometry. Increasing wing sweep and leading edge bluntness above a sweep angle of approximately 20 deg decreased the transition Reynolds number at all test Mach numbers.
Author : W. F. Lindsey
Publisher :
Page : 24 pages
File Size : 40,85 MB
Release : 1954
Category : Aerodynamics
ISBN :
Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.
Author : Don W. Jillie
Publisher :
Page : 36 pages
File Size : 31,13 MB
Release : 1961
Category : Fluid mechanics
ISBN :
Author : Robert W. Dunning
Publisher :
Page : 692 pages
File Size : 25,88 MB
Release : 1955
Category : Aerodynamics, Supersonic
ISBN :
The data showed that transition always occurred along a front parallel to the wing leading edge, and that increasing the leading-edge sweep angle or increasing the angle of attack between the undisturbed stream and model surface caused the transition line to move closer to the wing leading edge and, in general, decreased the transition Reynolds number.
Author : Samuel Ralph Pate
Publisher :
Page : 95 pages
File Size : 18,15 MB
Release : 1965
Category :
ISBN :
