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| Keywords: FAA-8083-3A Fig 15-9.png Transonic flow patterns svg High speed airplanes designed for subsonic flight are limited to some Mach number below the speed of sound to avoid the formation of shock waves that begin to develop as the airplane nears Mach 1 0 These shock waves and the adverse effects associated with them can occur when the airplane speed is substantially below Mach 1 0 The Mach speed at which some portion of the airflow over the wing first equals Mach 1 0 is termed the critical Mach number MACHCRIT This is also the speed at which a shock wave first appears on the airplane There is no particular problem associated with the acceleration of the airflow up to the point where Mach 1 0 is encountered; however a shock wave is formed at the point where the airflow suddenly returns to subsonic flow This shock wave becomes more severe and moves aft on the wing as speed of the wing is increased and eventually flow separation occurs behind the well-developed shock wave Figure 15-9 2004 http //www faa gov/library/manuals/aircraft/airplane_handbook/ Airplane Flying Handbook U S Government Printing Office Washington D C U S Federal Aviation Administration p 15-7 FAA-8083-3A PD-USGov Shock waves Aerodynamics diagrams Flow separation Diagrams of fluid flow past airfoils | ||||
