MAE3293 Compressible Aerodynamics Calculator

Ratio of Specific Heats (γ)

Calculate from:

Input Value:

Results

Mach Number (M)

–

p₀/p

–

ρ₀/ρ

–

T₀/T

–

A/A*

–

Calculate from:

Input Value:

Results

M₁

–

M₂

–

p₂/p₁

–

ρ₂/ρ₁

–

T₂/T₁

–

p₀₂/p₀₁

–

p₀₂/p₁

–

Enter any two values to calculate the third.

Mach number M₁

Deflection angle θ (deg)

Shock angle β (deg)

Results

M₁ₙ

–

M₂ₙ

–

M₂

–

p₂/p₁

–

ρ₂/ρ₁

–

T₂/T₁

–

p₀₂/p₀₁

–

Wave Geometry

Geometry: β is the shock angle; θ is the flow deflection angle.

Upstream Mach number M₁

Expansion angle θ (deg)

Results

ν(M₁) (deg)

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μ₁ (deg)

–

ν(M₂) (deg)

–

μ₂ (deg)

–

M₂

–

p₂/p₁

–

ρ₂/ρ₁

–

T₂/T₁

–

Freestream Mach (M₁)

Wedge Half-Angle (δ deg)

Angle of Attack (α deg)

Final Pressures

P_lower / P₁

–

P_upper / P₁

–

Wave Geometry

Intermediate Steps (Lower Surface)

Type

Shock

Deflection θ_lower (δ + α)

–

Shock Angle β_lower

–

M₁ₙ

–

M₂

–

Intermediate Steps (Upper Surface)

Type

Shock

Deflection θ_upper (δ - α)

–

Shock Angle β_upper

–

M₁ₙ

–

M₂

–

Type

Expansion

Expansion Angle θ_upper (α - δ)

–

ν(M₁)

–

ν(M₂)

–

M₂

–

Type

Aligned Flow

Deflection Angle (δ - α)

0.00

M₂

–