Pressure Distribution Tests of Several Sharp Leading Edge Wings, Bodies, and Body-wing Combinations at Mach 5 and 8 PDF Download
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Author: R. E. Randall Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 124
Book Description
Pressure distribution data were obtained on several sharp leading edge wings, conical bodies, and body-wing combinations at Mach 5 and 8. Shadowgraphs of shock wave and boundary layer phenomena were obtained at various angles of attack. Vapor screen photographs were taken with liquefied flow conditions in the test section to visualize the cross-sectional shape of the shock wave.
Author: R. E. Randall Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 124
Book Description
Pressure distribution data were obtained on several sharp leading edge wings, conical bodies, and body-wing combinations at Mach 5 and 8. Shadowgraphs of shock wave and boundary layer phenomena were obtained at various angles of attack. Vapor screen photographs were taken with liquefied flow conditions in the test section to visualize the cross-sectional shape of the shock wave.
Author: P. C. SHELTON Publisher: ISBN: Category : Languages : en Pages : 27
Book Description
Pressure distribution tests were made on a delta wing model and two wing-body combinations, all with sharp leading edges, in tunnel Hotshot 2 at a Mach number of 21 and a Reynolds number per foot of 400,000. Angle of attack ranged from -5 to +20 deg. Typical spanwise pressure distributions on the flat lower surface of model W4 are shown. It is observed that the pressure increases near the leading edge. The effect of adding the body to model W4 to obtain model W4B1 increases the pressure considerably over the entire lower surface. The spanwise pressure distribution of model (W-B)1 on the upper and lower surfaces is also shown. (Author).
Author: R. L. Palko Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 68
Book Description
Results are presented for tests conducted on a 1.5 elliptic cone to determine the pressure distribution, flow streamlines, and shock wave shape at high angles of attack. The tests were performed at a Mach number of 10 and a freestream unit Reynolds number of 1.6 x 10 to the 6th power per foot. The angle-of-attack range was from 0 to 60 deg. The model was oriented both with the major and the minor axis of the ellipse located in the pitch plane.
Author: Jack L. Burk Publisher: ISBN: Category : Boundary layer Languages : en Pages : 78
Book Description
Tests were conducted at Mach numbers 5, 6, and 8 to obtain force and pressure distribution data for two elliptic ogives. The results presented show the effect of Mach number and Reynolds number variation on aerodynamic forces for angles of attack from -6 to +6 deg and on pressure distributions for angles of attack from -4 to +4 deg. Shadowgraphs obtained at various angles of attack show shock wave and boundary layer phenomena.
Author: R. E. Randall
Author: R. E. Randall
Author: United States. Wright Air Development Division
Author: James R. Batt
Author: P. C. SHELTON
Author: 
Author: R. L. Palko
Author: Jack L. Burk
Author: Sandia Corporation
Author: Frank S. Malvestuto (Jr.)
Author: