The hypersonic viscous effect on a flat plate with finite leading edge
- 1 January 1959
- journal article
- research article
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 5 (02), 242-256
- https://doi.org/10.1017/s0022112059000179
Abstract
A method has been developed for calculating the viscous effects of the hypersonic flow on the fore part of various bodies. This method takes into account the finite leading-edge thickness of the body and the detached shock wave. The calculated pressure distributions agree with all experimental results for both air and helium over a wide range of Mach numbers and Reynolds numbers. The calculation predicts skin frictions of the order of twice those predicted by ordinary boundary-layer theory.Keywords
This publication has 9 references indexed in Scilit:
- An Experimental Investigation of Leading-Edge Shock-Wave - Boundary-Layer Interaction at Mach 5.8Journal of the Aeronautical Sciences, 1957
- Fluid Dynamic Effects at Speeds From M = 11 to 15Journal of the Aeronautical Sciences, 1956
- Viscous and Leading-Edge Thickness Effects on the Pressures on the Surface of a Flat Plate in Hypersonic FlowJournal of the Aeronautical Sciences, 1954
- On Strong Interaction for the Hypersonic Boundary Layer on an Inclined WedgeJournal of the Aeronautical Sciences, 1953
- Hypersonic Viscous Flow over an Inclined WedgeJournal of the Aeronautical Sciences, 1953
- Shock-Wave Effects on the Laminar Skin Friction of an Insulated Flat Plate at Hypersonic SpeedsJournal of the Aeronautical Sciences, 1953
- On the Flow of an Incompressible Viscous Fluid Past a Flat Plate at Moderate Reynolds NumbersJournal of Mathematics and Physics, 1953
- An Estimate of Viscosity Effect on the Hypersonic Flow Over an Insulated WedgeJournal of Mathematics and Physics, 1952
- Results of Recent Hypersonic and Unsteady Flow Research at the Langley Aeronautical LaboratoryJournal of Applied Physics, 1950