Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 200+ more calculators!
Sai Venkata Phanindra Chary Arendra
Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad
Sai Venkata Phanindra Chary Arendra has verified this Calculator and 100+ more calculators!

6 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
Coefficient of pressure with similarity parameters
Pressure coefficient=(2*(Flow Deflection angle)^2)*(((Specific Heat Ratio+1)/4)+sqrt((((Specific Heat Ratio+1)/4)^2)+(1/(Hypersonic similarity parameter)^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
Deflection angle
deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock)) 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
Hypersonic similarity parameter
Hypersonic similarity parameter=Mach Number*Flow Deflection angle GO

1 Other formulas that calculate the same Output

Component of downstream Mach no. normal to oblique shock for given normal upstream Mach no.
Downstream mach normal to oblique shock=sqrt((1+0.5*((Specific heat ratio-1)*Component of upstream mach normal to oblique shock^2))/(Specific heat ratio*Component of upstream mach normal to oblique shock^2-0.5*(Specific heat ratio-1))) GO

Component of Downstream Mach normal to oblique shock Formula

Downstream mach normal to oblique shock=Mach Number behind shock*sin(Oblique shock angle-Flow Deflection angle)
M<sub>n2</sub>=M<sub>2</sub>*sin(β-θ)
More formulas
Component of Upstream 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

Is it possible to correlate Oblique and Normal Shock?

It is always possible to convert an oblique shock into a normal shock by a Galilean transformation. In physics, a Galilean transformation is used to transform between the coordinates of two reference frames which differ only by constant relative motion within the constructs of Newtonian physics.

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

Component of Downstream Mach normal to oblique shock calculator uses Downstream mach normal to oblique shock=Mach Number behind shock*sin(Oblique shock angle-Flow Deflection angle) to calculate the Downstream mach normal to oblique shock, The Component of Downstream Mach normal to oblique shock is a function of Mach number downstream of oblique shock, oblique shock angle, and flow deflection angle. Downstream mach normal to oblique shock and is denoted by Mn2 symbol.

How to calculate Component of Downstream Mach normal to oblique shock using this online calculator? To use this online calculator for Component of Downstream Mach normal to oblique shock, enter Mach Number behind shock (M2), Oblique shock angle (β) and Flow Deflection angle (θ) and hit the calculate button. Here is how the Component of Downstream Mach normal to oblique shock calculation can be explained with given input values -> 0.109242 = 0.5*sin(3437.74677078559-30.3667631419393).

FAQ

What is Component of Downstream Mach normal to oblique shock?
The Component of Downstream Mach normal to oblique shock is a function of Mach number downstream of oblique shock, oblique shock angle, and flow deflection angle and is represented as Mn2=M2*sin(β-θ) or Downstream mach normal to oblique shock=Mach Number behind shock*sin(Oblique shock angle-Flow Deflection angle). Mach Number behind shock is the Mach number over the body after a shockwave has occurred, Oblique shock angle is defined as the angle between the shock and the resultant velocity upstream of the shock and Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock.
How to calculate Component of Downstream Mach normal to oblique shock?
The Component of Downstream Mach normal to oblique shock is a function of Mach number downstream of oblique shock, oblique shock angle, and flow deflection angle is calculated using Downstream mach normal to oblique shock=Mach Number behind shock*sin(Oblique shock angle-Flow Deflection angle). To calculate Component of Downstream Mach normal to oblique shock, you need Mach Number behind shock (M2), Oblique shock angle (β) and Flow Deflection angle (θ). With our tool, you need to enter the respective value for Mach Number behind shock, Oblique shock angle and Flow Deflection angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Downstream mach normal to oblique shock?
In this formula, Downstream mach normal to oblique shock uses Mach Number behind shock, Oblique shock angle and Flow Deflection angle. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Downstream mach normal to oblique shock=sqrt((1+0.5*((Specific heat ratio-1)*Component of upstream mach normal to oblique shock^2))/(Specific heat ratio*Component of upstream mach normal to oblique shock^2-0.5*(Specific heat ratio-1)))
Share Image
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!