Prandtl Meyer function at upstream Mach no. Calculator

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Physics	Gas Dynamics ↺
Gas-Dynamics	Oblique Shock and Expansion Waves ↺

✖The Specific heat ratio is the ratio of the heat capacity at constant pressure to heat capacity at constant volume.ⓘ Specific heat ratio [κ]			+10% -10%
✖Mach Number ahead of shock is the Mach number over the body before a shockwave has occurred ⓘ Mach Number ahead of shock [M₁]			+10% -10%

✖Prandtl Meyer function at upstream Mach no. is obtained by substituting upstream Mach number in Prandtl Meyer functionⓘ Prandtl Meyer function at upstream Mach no. [ν(M₁)]

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Prandtl Meyer function at upstream Mach no.

Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has created this Calculator and 100+ more calculators!

Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has verified this Calculator and 100+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Isentropic temperature 1 given specific volume

Isentropic temperature 1 given specific volume=Temperature of surface 2/(Specific volume at point 1/Specific volume at point 2)^(Specific heat ratio-1) GO

Isentropic temperature 2 given specific volume

Isentropic temperature 2 given specific volume=Temperature of surface 1*(Specific volume at point 1/Specific volume at point 2)^(Specific heat ratio-1) GO

Isentropic temperature 2 given pressure ratio

Isentropic temperature 2 given pressure ratio=Temperature of surface 1*(pressure 2/pressure 1)^((Specific heat ratio-1)/Specific heat ratio) GO

Isentropic temperature 1 given pressure ratio

Isentropic temperature 1 given pressure ratio=Temperature of surface 2/(pressure 2/pressure 1)^((Specific heat ratio-1)/Specific heat ratio) GO

Temperature Ratio when Isentropic Specific Volume is Given

Temperature ratio isentropic specific volume=(Specific volume at point 1/Specific volume at point 2)^(Specific heat ratio-1) GO

Isentropic Pressure at point 2

Isentropic Pressure at point 2 =pressure 1*(Specific volume at point 1/Specific volume at point 2)^Specific heat ratio GO

Isentropic Pressure at point 1

Isentropic Pressure at point 1=pressure 2/(Specific volume at point 1/Specific volume at point 2)^Specific heat ratio GO

Pressure Ratio in Isentropic Process

Pressure ratio isentropic process=(Specific volume at point 1/Specific volume at point 2)^Specific heat ratio GO

Temperature Ratio When Isentropic Pressure is Given

Temperature ratio isentropic pressure=(pressure 2/pressure 1)^((Specific heat ratio-1)/Specific heat ratio) GO

Deflection angle

deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock)) GO

Relation between Characteristic Mach number and Mach number

Characteristic Mach number=((Specific heat ratio+1)/((Specific heat ratio-1)+(2/(Mach Number^2))))^0.5 GO

Prandtl Meyer function at upstream Mach no. Formula

Prandtl Meyer Function at upstream Mach no.=sqrt((Specific heat ratio+1)/(Specific heat ratio-1))*atan(sqrt(((Specific heat ratio-1)*((Mach Number ahead of shock^2)-1))/(Specific heat ratio+1)))-atan(sqrt(((Mach Number ahead of shock^2)-1)))
ν(M1)=sqrt((κ+1)/(κ-1))*atan(sqrt(((κ-1)*((M1^2)-1))/(κ+1)))-atan(sqrt(((M1^2)-1)))

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Component of Upstream Mach normal to oblique shock GO

Component of Downstream Mach normal to oblique shock GO

Flow deflection angle GO

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Pressure ratio across the oblique shock GO

Temperature ratio across the oblique shock GO

Component of downstream Mach no. normal to oblique shock for given normal upstream Mach no. GO

Density behind oblique shock for given upstream density & normal upstream Mach no. GO

Pressure behind oblique shock for given upstream pressure & normal upstream Mach no GO

Temperature behind oblique shock for given upstream temperature & normal upstream Mach no. GO

Pressure ratio across the expansion fan GO

Temperature ratio across the expansion fan GO

Pressure behind expansion fan GO

Temperature behind expansion fan GO

Forward Mach angle of expansion fan GO

Rearward Mach angle of the expansion fan GO

Prandtl Meyer function GO

Flow deflection angle in terms of Prandtl Meyer function GO

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Snell's law is implemented for flow visualization by an optical system. According to Snell's law, a light ray, passing through a nonhomogeneous refracted field, is deflected from its original direction and a light path is different from that of an undisturbed ray. If a recording plane is placed in front of the light ray, after disturbing media, three quantities can be measured: the vertical displacement of the disturbed ray, the angular deflection of the disturbed ray with respect to the undisturbed one and the phase shift between both rays, owning to their different optical path lengths.

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How to Calculate Prandtl Meyer function at upstream Mach no.?

Prandtl Meyer function at upstream Mach no. calculator uses Prandtl Meyer Function at upstream Mach no.=sqrt((Specific heat ratio+1)/(Specific heat ratio-1))*atan(sqrt(((Specific heat ratio-1)*((Mach Number ahead of shock^2)-1))/(Specific heat ratio+1)))-atan(sqrt(((Mach Number ahead of shock^2)-1))) to calculate the Prandtl Meyer Function at upstream Mach no., The Prandtl Meyer function at upstream Mach no. formula is obtained by substituting the upstream Mach number in Prandtl Meyer function. Prandtl Meyer Function at upstream Mach no. and is denoted by ν(M₁) symbol.

How to calculate Prandtl Meyer function at upstream Mach no. using this online calculator? To use this online calculator for Prandtl Meyer function at upstream Mach no., enter Specific heat ratio (κ) and Mach Number ahead of shock (M₁) and hit the calculate button. Here is how the Prandtl Meyer function at upstream Mach no. calculation can be explained with given input values -> 0.208722 = sqrt((1.392758+1)/(1.392758-1))*atan(sqrt(((1.392758-1)*((1.5^2)-1))/(1.392758+1)))-atan(sqrt(((1.5^2)-1))).

FAQ

What is Prandtl Meyer function at upstream Mach no.?

The Prandtl Meyer function at upstream Mach no. formula is obtained by substituting the upstream Mach number in Prandtl Meyer function and is represented as ν(M₁)=sqrt((κ+1)/(κ-1))*atan(sqrt(((κ-1)*((M₁^2)-1))/(κ+1)))-atan(sqrt(((M₁^2)-1))) or Prandtl Meyer Function at upstream Mach no.=sqrt((Specific heat ratio+1)/(Specific heat ratio-1))*atan(sqrt(((Specific heat ratio-1)*((Mach Number ahead of shock^2)-1))/(Specific heat ratio+1)))-atan(sqrt(((Mach Number ahead of shock^2)-1))). The Specific heat ratio is the ratio of the heat capacity at constant pressure to heat capacity at constant volume and Mach Number ahead of shock is the Mach number over the body before a shockwave has occurred .

How to calculate Prandtl Meyer function at upstream Mach no.?

The Prandtl Meyer function at upstream Mach no. formula is obtained by substituting the upstream Mach number in Prandtl Meyer function is calculated using Prandtl Meyer Function at upstream Mach no.=sqrt((Specific heat ratio+1)/(Specific heat ratio-1))*atan(sqrt(((Specific heat ratio-1)*((Mach Number ahead of shock^2)-1))/(Specific heat ratio+1)))-atan(sqrt(((Mach Number ahead of shock^2)-1))). To calculate Prandtl Meyer function at upstream Mach no., you need Specific heat ratio (κ) and Mach Number ahead of shock (M₁). With our tool, you need to enter the respective value for Specific heat ratio and Mach Number ahead of shock and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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