Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Static enthalpy ratio across a normal shock
Static enthalpy ratio across shock=(1+((2*Specific heat ratio)/(Specific heat ratio+1))*((Mach Number ahead of shock^2)-1))/((Specific heat ratio+1)*(Mach Number ahead of shock^2)/(2+((Specific heat ratio-1)*(Mach Number ahead of shock^2)))) GO
Temperature ratio across a normal shock
Temperature ratio across shock=(1+((2*Specific heat ratio)/(Specific heat ratio+1))*((Mach Number ahead of shock^2)-1))/((Specific heat ratio+1)*(Mach Number ahead of shock^2)/(2+((Specific heat ratio-1)*(Mach Number ahead of shock^2)))) GO
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
Density ratio across a normal shock
Density ratio across shock=(Specific heat ratio+1)*(Mach Number ahead of shock^2)/(2+((Specific heat ratio-1)*(Mach Number ahead of shock^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
Pressure ratio for high Mach number
pressure ratio=(Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Pressure ratio across a normal shock
Pressure ratio across shock=1+((2*Specific heat ratio)/(Specific heat ratio+1))*((Mach Number ahead of shock^2)-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
Deflection angle
deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock)) GO
Shock strength
Shock Strength=(2*Specific heat ratio/(1+Specific heat ratio))*((Mach Number ahead of shock^2)-1) GO

Component of Upstream Mach normal to oblique shock Formula

Component of upstream mach normal to oblique shock=Mach Number ahead of shock*sin(Oblique shock angle)
M<sub>n1</sub>=M<sub>1</sub>*sin(β)
More formulas
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
Prandtl Meyer function at upstream Mach no. GO

What is an Oblique Shock?

An oblique shock wave is a shock wave that, unlike a normal shock, is inclined with respect to the incident upstream flow direction. It will occur when a supersonic flow encounters a corner that effectively turns the flow into itself and compresses.

How to Calculate Component of Upstream Mach normal to oblique shock?

Component of Upstream Mach normal to oblique shock calculator uses Component of upstream mach normal to oblique shock=Mach Number ahead of shock*sin(Oblique shock angle) to calculate the Component of upstream mach normal to oblique shock, The Component of Upstream Mach normal to oblique shock is the product of the Upstream Mach number and the oblique shock angle. Component of upstream mach normal to oblique shock and is denoted by Mn1 symbol.

How to calculate Component of Upstream Mach normal to oblique shock using this online calculator? To use this online calculator for Component of Upstream Mach normal to oblique shock, enter Mach Number ahead of shock (M1) and Oblique shock angle (β) and hit the calculate button. Here is how the Component of Upstream Mach normal to oblique shock calculation can be explained with given input values -> -0.457216 = 1.5*sin(3437.74677078559).

FAQ

What is Component of Upstream Mach normal to oblique shock?
The Component of Upstream Mach normal to oblique shock is the product of the Upstream Mach number and the oblique shock angle and is represented as Mn1=M1*sin(β) or Component of upstream mach normal to oblique shock=Mach Number ahead of shock*sin(Oblique shock angle). Mach Number ahead of shock is the Mach number over the body before a shockwave has occurred and Oblique shock angle is defined as the angle between the shock and the resultant velocity upstream of the shock.
How to calculate Component of Upstream Mach normal to oblique shock?
The Component of Upstream Mach normal to oblique shock is the product of the Upstream Mach number and the oblique shock angle is calculated using Component of upstream mach normal to oblique shock=Mach Number ahead of shock*sin(Oblique shock angle). To calculate Component of Upstream Mach normal to oblique shock, you need Mach Number ahead of shock (M1) and Oblique shock angle (β). With our tool, you need to enter the respective value for Mach Number ahead of shock and Oblique shock angle 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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