2 Aerodynamics
131
Fig. 2.67 Shock formed by fighter jet nozzle
Fig. 2.68 Control body in relative coordinates
The momentum equation is applied to the dotted control surface
−ρ 1 V
2
1 + ρ 2 V
2
2 = p 1 − p 2
From the energy equation of adiabatic flow
V
2
1 +
2
γ − 1
a
2
1 = V
2
2 +
2
γ − 1
a
2
2 =
γ + 1
γ − 1
a
2
∗
131
Fig. 2.67 Shock formed by fighter jet nozzle
Fig. 2.68 Control body in relative coordinates
The momentum equation is applied to the dotted control surface
−ρ 1 V
2
1 + ρ 2 V
2
2 = p 1 − p 2
From the energy equation of adiabatic flow
V
2
1 +
2
γ − 1
a
2
1 = V
2
2 +
2
γ − 1
a
2
2 =
γ + 1
γ − 1
a
2
∗