Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 300+ more calculators!
Rushi Shah
K J Somaiya College of Engineering (K J Somaiya), Mumbai
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11 Other formulas that you can solve using the same Inputs

Flow deflection angle
Flow Deflection angle=atan((2*cot(Oblique shock angle)*(((Mach Number ahead of shock*sin(Oblique shock angle))^2)-1))/(((Mach Number ahead of shock^2)*(Specific heat ratio+cos(2*Oblique shock angle)))+2)) GO
Mach Number behind the shock
Mach Number behind shock=((2+(Specific heat ratio*(Mach Number ahead of shock^2))-(Mach Number ahead of shock^2))/((2*Specific heat ratio*(Mach Number ahead of shock^2))-Specific heat ratio+1))^(1/2) GO
Velocity behind a normal shock
Velocity downstream of shock=Velocity upstream of shock/((Specific heat ratio+1)/((Specific heat ratio-1)+(2/(Mach Number ahead of shock^2)))) GO
Ratio of stagnation and static pressure
Stagnation to Static Pressure=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Component of Downstream Mach normal to oblique shock
Downstream mach normal to oblique shock=Mach Number behind shock*sin(Oblique shock angle-Flow Deflection angle) GO
Ratio of Stagnation and Static Density
Stagnation to Static Density=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(1/(Specific Heat Ratio-1)) GO
Component of Upstream Mach normal to oblique shock
Component of upstream mach normal to oblique shock=Mach Number ahead of shock*sin(Oblique shock angle) GO
Shock strength
Shock Strength=(2*Specific heat ratio/(1+Specific heat ratio))*((Mach Number ahead of shock^2)-1) GO
Mach number
Mach Number=Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*final temp.)) GO
Ratio of Stagnation and Static Temperature
Stagnation to Static Temperature=1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)) GO
Speed of Sound
Speed of Sound=sqrt(Specific Heat Ratio*[R-Dry-Air]*Temperature of Gas) GO

Deflection angle Formula

deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock))
θ=(2/(γ-1))*((1/M<sub>1</sub>)-(1/M<sub>2</sub>))
More formulas
Mach number GO
Dynamic pressure GO
lift coefficient GO
Lift Force GO
Coefficient of drag GO
Drag force GO
Dynamic pressure based on coefficient of lift GO
Normal Force Coefficient GO
Moment coefficient GO
Shear-stress distribution. GO
Axial force coefficient GO
Fourier’s law of heat conduction GO
Hypersonic similarity parameter GO
Coefficient of pressure with similarity parameters GO
Pressure ratio for high Mach number GO
Mach ratio at high mach number GO
Pressure ratio having high mach number with similarity constant GO
Newtonian sine-squared law for pressure coefficient GO
Supersonic expression for pressure coefficient on a surface with local deflection angle θ GO

what is deflection angle?

Equation is the hypersonic relation for Prandtl–Meyer expansion waves; it is an approximate relation that becomes more accurate as M1 and M2 become larger

How to Calculate Deflection angle?

Deflection angle calculator uses deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock)) to calculate the deflection angle, Deflection angle is the product of inverse of specific heat ratio minus 1 and double the inverse change in velocity of flow usually in mach number. deflection angle and is denoted by θ symbol.

How to calculate Deflection angle using this online calculator? To use this online calculator for Deflection angle, enter Specific Heat Ratio (γ), Mach Number ahead of shock (M1) and Mach Number behind shock (M2) and hit the calculate button. Here is how the Deflection angle calculation can be explained with given input values -> -4.444444 = (2/(1.6-1))*((1/1.5)-(1/0.5)).

FAQ

What is Deflection angle?
Deflection angle is the product of inverse of specific heat ratio minus 1 and double the inverse change in velocity of flow usually in mach number and is represented as θ=(2/(γ-1))*((1/M1)-(1/M2)) or deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock)). The Specific heat ratio of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume, Mach Number ahead of shock is the Mach number over the body before a shockwave has occurred and Mach Number behind shock is the Mach number over the body after a shockwave has occurred.
How to calculate Deflection angle?
Deflection angle is the product of inverse of specific heat ratio minus 1 and double the inverse change in velocity of flow usually in mach number is calculated using deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock)). To calculate Deflection angle, you need Specific Heat Ratio (γ), Mach Number ahead of shock (M1) and Mach Number behind shock (M2). With our tool, you need to enter the respective value for Specific Heat Ratio, Mach Number ahead of shock and Mach Number behind 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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