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
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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(M<sub>1</sub>)=sqrt((κ+1)/(κ-1))*atan(sqrt(((κ-1)*((M<sub>1</sub>^2)-1))/(κ+1)))-atan(sqrt(((M<sub>1</sub>^2)-1)))
More formulas
Component of Upstream Mach normal to oblique shock GO
Component of Downstream Mach normal to oblique shock GO
Flow deflection angle GO
Density ratio across the oblique shock GO
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

Which law is implemented for flow visualization by optical system?

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.

What are methods of flow visualization?

Flow visualization is essential for exploring, and understanding fluid behaviour and can be both qualitative and quantitative. The main methods for visualization of these flows are optical methods. The three principal optical methods are shadow, schlieren and interferometry.

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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