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17 January, 05:18

The inlet for a high-bypass-ratio turbofan engine has an area A1 of 6.0 m 2 and is designed to have an inlet Mach number M~ of 0.6. Determine the additive drag at the flight conditions of sea-level static test and Mach number of 0.8 at 12-km altitude.

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  1. 17 January, 05:24
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    The additive drag at flight condition will be found by the following equation

    Area = A1 = 6m2

    Da = Additive drag

    Cda = Additive drag coefficient

    P = prassure at altitude of 12Km

    Po = Prassure at sea level

    /gamma = Ratio of specific heat capacity

    The formula of additive drag is given below

    D = Cda q A

    q = Dynamic prassure, A = cross sectional area

    q = (/gamma / 2) P0 M02

    D = Cda (/gamma/2) po Mo2 A

    Cda=0.32

    /gamma=1.4

    M=0.8

    p0 = 101325pa

    D = 0.32 (1.4/2) (101325pa) (0.6) 2 6

    D = 49025N

    Explanation:

    The additive drag at the flight conditions will be D = 49025N
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