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.

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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