The Blunt Plate In Hypersonic Flow
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The Blunt Plate in Hypersonic Flow
Author | : Donald Louis Baradell |
Publisher | : |
Total Pages | : 54 |
Release | : 1960 |
Genre | : Fluid mechanics |
ISBN | : |
An Approximate Method for Calculating Surface Pressures on Curved Profile Blunt Plates in Hypersonic Flow
Author | : Marcus O. Creager |
Publisher | : |
Total Pages | : 32 |
Release | : 1959 |
Genre | : Numerical analysis |
ISBN | : |
Pressure and Heat Transfer on Blunt Curved Plates with Concave and Convex Surfaces in Hypersonic Flow
Author | : Davis H. Crawford |
Publisher | : |
Total Pages | : 68 |
Release | : 1968 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Hypersonic Flow Over a Blunt Flat Plate with a Trailing Edge Flap
Author | : George David Katz |
Publisher | : |
Total Pages | : 164 |
Release | : |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
The Flow about the Leading Edge of a Swept Blunt Plate at Hypersonic Speeds
Author | : C. C. Horstman |
Publisher | : |
Total Pages | : 36 |
Release | : 1962 |
Genre | : Fluid mechanics |
ISBN | : |
An Experimental Investigation of the Surface Pressure and the Laminar Boundary Layer on a Blunt Flat Plate in Hypersonic Flow: Surface pressure distributions on a blunted flat plate
Author | : G. M. Gregorek |
Publisher | : |
Total Pages | : 124 |
Release | : 1963 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Vol. 1 Pressures were measured over the surface of an unswept blunt flat plate having a cylindrical leading edge 1/2-inch in diameter. The flat plate was side-mounted in the ALOSU 12-inch continuous hypersonic wind tunnel. Separate tests were conducted with cylinders in order to obtain detailed data for the leading-edge. Stagnation temperatures were sufficiently high to eliminate condensation effects. The leading edge and cylinder pressure ratios were noted to be independent of both Mach number and Reynolds number. The flat plate pressure ratios show a small dependence on Mach number. Reynolds number effects on the plate pressure ratios were small except at the lower levels of Reynolds number where the interaction of the thickened boundary layer caused increases in pressure.
The Blunt-leading-edge Problem in Hypersonic Flow
Author | : HakurÅ Oguchi |
Publisher | : |
Total Pages | : 1 |
Release | : 1961 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Study was made of the hypersonic flow over a flat plate with a blunt nose. The analysis is based on the flow model in which the flow field behind the shock wave may be divided into two regions: (1) the inviscid-hypersonic-flow region and (2) the entropy layer, across which the pressure undergoes no appreciable change. (Author).