1. Using the Second and Third-Order Approximations, find the pressure acting on the upper and lower surfacesof a flat plate inclined at an angle of 10° toward the airflow at initial Mach number of 2 and freestreampressure of 1 atm.

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Answered: 1. Using the Second and Third-Order…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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4. It is important to remember that the isentropic relations and normal shock relationsare monotonic with Mach number and can be inverted. To illustrate this, consider thefollowing problems, (c) If the temperature jumps from 0 Celsius ahead of a shock to 200 Celsius behinda shock, what is the shock Mach number?(d) If the velocity behind a Mach 5 shock wave is 200 m/s, what is the upstreamvelocity?
A normal shock occurs in a stream of oxygen. The oxygen flows at Ma=1.8 and the upstream pressure and temperature are 40 psia and 85 degrees Fahrenheit. a) Calculate the following on the downstream side of the shock: static pressure, stagnation pressure, static temperature, stagnation temperature, static density, and velocity. b)If the Mach number is doubled to 3.6, what will be the resulting values of the parameters listed in part (a)?
Question : Air undergoes isentropic compression from the initial temperature and pressure T1 = 25°C and P1 = 100 kPa to the final pressure P2 = 500 kPa. Find the final temperature T2 (in Celsius). Justify your answer and show your work
The velocity ratio(v1/v2)of an isentropic flow through a supersonic wind tunnel is 0.915 ifthe velocity and mach number at the exit are 376.95 m/s and 2.60 respectively find the value of speed of sound at the entrance
QUESTION 14 The fan of a turbofan engine is tested at high speed. The flow approaches the fan tip at a relative Mach number M1rel = 1.19. An oblique shock forms at the fan tip leading edge, with a shock angle B = 87 degrees. Use cold-air- standard assumptions and the two-dimensional oblique shock formulae to determine the relative Mach number M2rel after the shock. State your answer to two decimal places. Partial credit is awarded for a reasonable approximation to the correct numerical answer. %3D

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1. Using the Second and Third-Order Approximations, find the pressure acting on the upper and lower surfaces of a flat plate inclined at an angle of 10° toward the airflow at initial Mach number of 2 and freestream pressure of 1 atm.