The impact of a shock-wave on a thin two-dimensional aerofoil moving at supersonic speed
- 1 January 1963
- journal article
- research article
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 15 (02) , 223-240
- https://doi.org/10.1017/s0022112063000197
Abstract
The pressure field is found in closed analytic form for the region behind an arbitrary plane shock, which has encountered a thin aerofoil moving at supersonic speed. The solution may be used for wedges at small incidence to the air-flow around them, and for wedges yawed with respect to the shock plane through angles up to a limiting value which always exceeds 67·8°. The pressure distribution on the surface of a wedge is calculated in a number of examples illustrating separately the effects of shock strength, wedge speed, and angle of yaw.Keywords
This publication has 4 references indexed in Scilit:
- A Linearized Analysis of the Forces Exerted on a Rigid Wing by a Shock WaveJournal of the Aerospace Sciences, 1959
- THE DIFFRACTION AND REFLECTION OF SHOCK WAVESThe Quarterly Journal of Mechanics and Applied Mathematics, 1954
- Diffraction of Blasts by Axisymmetric BodiesJournal of the Aeronautical Sciences, 1952
- Aerodynamics of BlastsJournal of the Aeronautical Sciences, 1951