Compressible Aerodynamics Calculator
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TR
TR
Isentropic Relations
Input Type
Mach Number
T/T₀
P/P₀
ρ/ρ₀
A/A* (subsonic)
A/A* (supersonic)
Mach Angle (°)
P-M Angle (°)
Value
Gamma
Compute
Mach Number
Mach Angle (°)
P-M Angle (°)
P / P₀
ρ / ρ₀
T / T₀
P / P*
ρ / ρ*
T / T*
A / A*
Normal Shock Relations
Input Type
M₁
M₂
P₂ / P₁
ρ₂ / ρ₁
T₂ / T₁
P₀₂ / P₀₁
P₁ / P₀₂
Value
Gamma
Compute
M₁
M₂
P₀₂ / P₀₁
P₁ / P₀₂
P₂ / P₁
ρ₂ / ρ₁
T₂ / T₁
Oblique Shock Relations
Gamma
Mach Number (M₁)
Input Type
Turn Angle (Weak Shock)
Turn Angle (Strong Shock)
Wave Angle
M₁n
Value
Compute
M₂
Turn Angle (°)
Wave Angle (°)
P₂ / P₁
ρ₂ / ρ₁
T₂ / T₁
P₀₂ / P₀₁
M₁n
M₂n
Conical Shock Relations
Gamma
Mach Number (M₁)
Input Type
Cone Angle (°)
Wave Angle (°)
Mach at Surface (Mc)
Value
Compute
Mc (surface)
Cone Angle (°)
Wave Angle (°)
Shock Turn Angle (°)
P₂ / P₁ (at shock)
P₀₂ / P₀₁
ρ₂ / ρ₁ (at shock)
T₂ / T₁ (at shock)
Pc / P₁ (surface)
P₀c / P₀₁
ρc / ρ₁ (surface)
Tc / T₁ (surface)
Fanno Flow
Input Type
Mach Number
T / T*
P / P*
P₀ / P₀* (subsonic)
P₀ / P₀* (supersonic)
U / U*
4fL* / D (subsonic)
4fL* / D (supersonic)
(s*−s) / R (subsonic)
(s*−s) / R (supersonic)
Value
Gamma
Compute
Mach Number
T / T*
P / P*
P₀ / P₀*
U / U*
4fL* / D
(s*−s) / R
Rayleigh Flow
Input Type
Mach Number
T₀ / T₀* (subsonic)
T₀ / T₀* (supersonic)
T / T* (below T_max)
T / T* (above T_max)
P / P*
P₀ / P₀* (subsonic)
P₀ / P₀* (supersonic)
U / U*
(s*−s) / R (subsonic)
(s*−s) / R (supersonic)
Value
Gamma
Compute
Mach Number
T₀ / T₀*
T / T*
P / P*
P₀ / P₀*
U / U*
(s*−s) / R
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Aytaç Arıkan