Download Aircraft and Rocket Propulsion by Brian J. Cantwell PDF

By Brian J. Cantwell

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Extra resources for Aircraft and Rocket Propulsion

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25) Now the range integral becomes w final hf L R = – η ov ------  ---- g  D ∫ dw ------- . 26) w initial The result is hf L  w initial R = η ov ------  ---- Log  ------------------ . 27) generally attributed to the French aircraft pioneer Louis Charles Breguet who in 1919 founded a commercial airline company that would eventually become Air France. This result highlights the key role played by the engine overall efficiency in determining aircraft range. Note that as the aircraft burns fuel it must increase altitude to maintain constant L ⁄ D .

A concentric shaft connects the high pressure turbine and compressor. 5 is generally taken at the interface between the low and high pressure compressor. Roll Royce turbofans commonly employ three spools with the high pressure compressor broken into two spools. Station 13 - This is a station in the bypass stream corresponding to the fan exit and the entrance to the fan exhaust nozzle. 53) Station 18 - The fan nozzle throat. Station 1e - The fan nozzle exit. 54) Station 3 - The exit of the high pressure compressor.

From the entrance to the end of the inlet there is generally an increase in area and so the component is appropriately called a diffuser. 5 - The inlet throat. Station 2 - The fan or compressor face. 51) Generally the flow from the reference state is regarded as adiabatic and isentropic so that T t1 = T t0 P t1 = P t0 . 52) The inlet is usually modeled as an adiabatic flow so the stagnation temperature is approximately constant however the stagnation pressure generally decreases due to the presence of viscous boundary layers and possibly shock waves.

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