Answer:
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
