Compressible Aerodynamics Calculator

Isentropic Flow Relations (for a Calorically Perfect Gas)

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M = 
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Mach angle (°) =
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Prandtl-Meyer angle (°) =
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p0/p =
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T0/T =
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ρ0/ρ =
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p/p* =
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T/T* =
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ρ/ρ* =
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A/A* =
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Normal Shock Relations (for a Calorically Perfect Gas)

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M1
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M2 =
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ρ21 =
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T2/T1 =
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p2/p1 =
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p0,2/p0,1 =
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p0,2/p1 =
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Oblique Shock Relations (for a Calorically Perfect Gas)

M1 =
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Deflection Angle (°) =
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Wave Angle (°) =
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Mn,1 =
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Mn,2 =
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M2 =
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p2/p1 =
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p0,2/p0,1 =
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ρ21 =
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T2/T1 =
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