Component of Upstream Mach normal to oblique shock Solution

STEP 0: Pre-Calculation Summary
Formula Used
Component of upstream mach normal to oblique shock = Mach Number ahead of shock*sin(Oblique shock angle)
Mn1 = M1*sin(β)
This formula uses 1 Functions, 3 Variables
Functions Used
sin - Trigonometric sine function, sin(Angle)
Variables Used
Component of upstream mach normal to oblique shock - Component of upstream mach normal to oblique shock is that component of upstream Mach number which is normal to oblique shockwave.
Mach Number ahead of shock - Mach Number ahead of shock is the Mach number over the body before a shockwave has occurred.
Oblique shock angle - (Measured in Radian) - Oblique shock angle is defined as the angle between the shock and the resultant velocity upstream of the shock.
STEP 1: Convert Input(s) to Base Unit
Mach Number ahead of shock: 1.5 --> No Conversion Required
Oblique shock angle: 60 Radian --> 60 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Mn1 = M1*sin(β) --> 1.5*sin(60)
Evaluating ... ...
Mn1 = -0.457215931653325
STEP 3: Convert Result to Output's Unit
-0.457215931653325 --> No Conversion Required
FINAL ANSWER
-0.457215931653325 <-- Component of upstream mach normal to oblique shock
(Calculation completed in 00.005 seconds)

Credits

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

10+ Oblique Shock and Expansion Waves Calculators

Temperature behind oblique shock for given upstream temperature and normal upstream Mach number
Temperature behind shock = Temperature ahead of shock*((1+((2*Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic+1))*((Component of upstream mach normal to oblique shock^2)-1))/((Specific Heat Ratio Dynamic+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific Heat Ratio Dynamic-1)*(Component of upstream mach normal to oblique shock^2))))) Go
Temperature Ratio across Oblique Shock
Temperature ratio across shock = (1+((2*Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic+1))*((Component of upstream mach normal to oblique shock^2)-1))/((Specific Heat Ratio Dynamic+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific Heat Ratio Dynamic-1)*(Component of upstream mach normal to oblique shock^2)))) Go
Pressure behind expansion fan
Pressure behind expansion fan = Pressure ahead expansion fan*((1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)))^((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1)) Go
Component of downstream Mach number normal to oblique shock for given normal upstream Mach number
Downstream Mach Normal to Oblique Shock = sqrt((1+0.5*((Specific Heat Ratio Dynamic-1)*Component of upstream mach normal to oblique shock^2))/(Specific Heat Ratio Dynamic*Component of upstream mach normal to oblique shock^2-0.5*(Specific Heat Ratio Dynamic-1))) Go
Pressure Ratio across Expansion Fan
Pressure ratio across expansion fan = ((1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)))^((Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic-1)) Go
Density behind oblique shock for given upstream density and normal upstream Mach number
Density behind shock = Density ahead of shock*((Specific Heat Ratio Dynamic+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific Heat Ratio Dynamic-1)*(Component of upstream mach normal to oblique shock^2)))) Go
Density Ratio across Oblique Shock
Density ratio across shock = (Specific Heat Ratio Dynamic+1)*(Component of upstream mach normal to oblique shock^2)/(2+((Specific Heat Ratio Dynamic-1)*(Component of upstream mach normal to oblique shock^2))) Go
Pressure behind oblique shock for given upstream pressure and normal upstream Mach number
Static pressure behind shock = Static pressure ahead of shock*(1+((2*Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic+1))*((Component of upstream mach normal to oblique shock^2)-1)) Go
Temperature Ratio across Expansion Fan
Temperature ratio across expansion fan = (1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. ahead expansion fan^2))/(1+0.5*(Specific Heat Ratio Dynamic-1)*(Mach no. behind expansion fan^2)) Go
Pressure Ratio across Oblique shock
Pressure ratio across shock = 1+((2*Specific Heat Ratio Dynamic)/(Specific Heat Ratio Dynamic+1))*((Component of upstream mach normal to oblique 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)
Mn1 = M1*sin(β)

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 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) & 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(60).

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 & 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) & Oblique shock angle (β). With our tool, you need to enter the respective value for Mach Number ahead of shock & Oblique shock angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
Share Image
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!