f16_sp - Fluids Lecture 16 Notes 1. Shock Losses 2....

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Unformatted text preview: Fluids Lecture 16 Notes 1. Shock Losses 2. Compressible-Flow Pitot Tube Reading: Anderson 8.6, 8.7 Shock Losses Stagnation pressure jump relation The stagnation pressure ratio across the shock is parenleftBigg 1 + 1 M 2 2 parenrightBigg / ( 1) p o 2 p 2 2 = p o 1 p 1 1 + 1 M 1 2 (1) 2 where both p 2 /p 1 and M 2 are functions of the upstream Mach number M 1 , as derived previ- ously. The figures show the p o 2 /p o 1 ratio, with the second figure showing an expanded scale near M 1 1. 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.0 1.2 1.4 1.6 1.8 2.0 2.2 2.4 2.6 2.8 3.0 po2/po1 M1 0.93 0.94 0.95 0.96 0.97 0.98 0.99 1.00 1.0 1.05 1.1 1.15 1.2 1.25 1.3 1.35 1.4 1.45 1.5 po2/po1 M1 The fractional shock total-pressure loss 1 p o 2 /p o 1 is seen to be small for M 1 close to unity, but increases rapidly for higher Mach numbers. Minimizing this loss is of great practical importance, since it cuts directly into the performance of supersonic air-breathing engines....
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.

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f16_sp - Fluids Lecture 16 Notes 1. Shock Losses 2....

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