Read e-book online Aircraft and Rocket Propulsion PDF

By Brian J. Cantwell

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60) In general the goal of the designer is to minimize heat loss and stagnation pressure loss through the inlet, burner and nozzle. There are two more very important parameters that need to be defined. The first is one we encountered before when we compared the fuel enthalpy to the ambient air enthalpy. 61) The second parameter is, in a sense the most important quantity needed to characterize the performance of an engine. 62) In general every performance measure of the engine gets better as τ λ is increased and a tremendous investment has been made over the years to devise turbine cooling schemes that permit ever higher turbine inlet temperatures T t4 .

17 3/21/11 Ramjet control  P te A e  γ m˙ e = -------------------------------------  ------------------- f ( M e ) = ( 1 + f )m˙ a γ+1 --------------------  γ RT te ( 2 γ + 1 γ – 1 )  ----------- 2  . 44) The pressure in the engine is likely to be very high at this free stream Mach number and so the nozzle is surely choked and we can write  P te A e  1 γ m˙ a = ------------------ -------------------------------------  ------------------- γ+1 (1 + f ) --------------------  γ RT te 2 ( γ + 1 γ – 1 )  ----------- 2  .

5 3 P0 4 e M0 = 3 shock and the stagnation temperature at station 4 is T t4 = 2000K . 5 = 8 , A 1 = A 3 = A 4 and A 4 ⁄ A e = 3 . Determine the dimensionless thrust T ⁄ ( P 0 A 1 ) . Do not assume f<<1. Neglect stagnation pressure losses due to wall friction and burner drag. Assume that the static pressure outside the nozzle has recovered to the ambient value. 5 = A 3 . By what proportion would the air mass flow change? Solution - The first point to recognize is that the stagnation pressure at station 4 exceeds the ambient by more than a factor of two - note the pressure outside the nozzle is assumed to have recovered to the ambient value.

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Aircraft and Rocket Propulsion by Brian J. Cantwell

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