The development of supersonic aerodynamic theory initially advanced concurrently with low‐speed aerodynamic theory since propeller aircraft that could reach speeds of 900 km h‐1 in steep diving flight experienced serious stability and control problems due to the compressibility of air. In the present world of large‐scale applications of high‐speed aircraft, designers involved in the development of a supersonic cruise vehicle should have a basic understanding of aerodynamic phenomena in high‐speed flight, such as shock and expansion waves. This chapter focuses on high speed flow phenomena around body shapes representative of aircraft components as well as applications of the theory. It includes information on atmospheric air compressibility, streamlines and mach waves, normal shock waves, planar oblique shock wave, and curved and detached shock waves. Expansions of a supersonic flow around a sharp corner or a curved surface deflected away from the oncoming flow are also illustrated.
Aerodynamic Phenomena in Supersonic Flow
2020-07-07
19 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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