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Shocks in fluids result from fluid flow that is more rapid than the speed of a compression wave. Thus there is no means for the flow to adjust gradually. Pressure, velocity, and temperatures change abruptly, causing severe fatigue and component destruction in military aircraft and engine turbines. This problem is not limited to supersonic aircraft; many parts of subsonic craft are supersonic. | Technical Report HL-93-12 August 1993 fVi i . . i . US Army Corps of Engineers Waterways Experiment Station In-House Laboratory Independent Research Program A Finite Element Scheme for Shock Capturing by R. c. Berger Jr. Hydraulics Laboratory Approved For Public Release Distribution Is Unlimited Prepared for Assistant Secretary of the Army R D The contents of this report are not to be used for advertising publication or promotional purposes. Citation of trade names does not constitute an official endorsement or approval of the use of such commercial products. PRINTED ON RECYCLED PAPER Technical Report HL-93-12 August 1993 In-House Laboratory Independent Research Program A Finite Element Scheme for Shock Capturing by R. c. Berger Jr. Hydraulics Laboratory U.S. Army Corps of Engineers Waterways Experiment station 3909 Halls Ferry Road Vicksburg MS 39180-6199 Final report Approved for public release distribution is unlimited Prepared for Assistant Secretary of the Army R D Washington DC .
