i need the answer quickly Question TwoAir flows in the duct shown in Figure. The first shock,which turns the flow 15°, is observed to form at a 40°angle. The flow is known to be supersonic in regions 1and 2 and subsonic in region 3.(a) Determine M3 and ß.(b) Determine the pressure ratios P3/P1 and po3/Po1.40°

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Answered: Air flows in the duct shown in Figure.…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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3. Assume a supersonic flow with M=2, P=1 atm, and T=288 K that is deflected via 15° at a compression corner. Determine M, P, T, as well as PO and TO behind the associated oblique shock wave.
A uniform supersonic airstream travelling at a Mach number of 9.0 passes over a concave corner, as shown in Figure 4. An oblique shockwave, which makes an angle of 30° with the flow direction, is attached to the corner under the given conditions. If the pressure and temperature in the uniform flow are 45 kPa and -30 °C respectively, determine the Mach number and deflection angle behind the wave.
The instrument fairing on an aircraft is shown below, consisting of a forward ramp at30◦, a horizontal section, and a rear ramp at 25◦. During a flight in air at Mach 5.5,the static pressure is 42.6 kPa and the static temperature is 250 K. An oblique shockforms at the turn of the forward ramp, two expansion fans form at the front and rear ofthe horizontal section, and a second oblique shock forms at the turn of the rear ramp. (a) Calculate the Mach numbers and pressures at regions 2, 3, 4, and 5. (b) Determine stagnation pressure ratio p05/p01. (c) Tabulate the angles of all oblique shocks waves leading/trailing expansion waves relative to horizontal (not relative to flow angle). Gamma = 1.4, R=287 J/kgK PLEASE SHOW ALL WORK
If the Mach number behind a normal shock is equal to 0.4, calculate the ratio of the readings of pitot tubes located before and after the shock.
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Q6/ Air is heated as it flows subsonically through a duct. When the amount of heat transfer reaches 60 kJ/kg, the flow is observed to be choked, and the velocity and the static pressure are measured to be 620 m/s and 270 kPa. Disregarding frictional losses, determine the velocity, static temperature, and static pressure at the duct inlet.
The driver and driven gases in a shock tube are both air at 300 K. Assume p4/p1 = 8.006. After the diaphragm is broken, an incident shock wave is propagating into the driven section and an incident expansion wave is propagating into the driver section. If the strength of the incident shock (p2/p1) is 2.6, a. Calculate the strength of the incident expansion wave (p3/p4). b. Calculate the induced mass motion velocity behind the expansion wave. c. Find the propagation velocity of the head expansion wave. d. Find the propagation velocity of the tail expansion wave.
A nozzle for a supersonic wind tunnel is designed to achieve a Mach number of 3.2, with a velocity of 2500 m/s, and a density of 1.0 kg/ m³ in the test section. Find the temperature and pressure in the test section and the upstream stagnation conditions. The fluid is helium. Te = i Pe= To= Po= Mi K kPa K kPa
Q11: Air enters the converging section shown in Figure and a normal shock occurs at the exit. The entering Mach number is 2.8 and the area ratio 1.7. Compute the overall static A1/A2 = temperature ratio T3/T1. Ans.: T3/T1 = 2.43 A,|A, = 1.7 M = 2.8
When a pitot-static tube is placed in a supersonic flow, the probe reads P = 190 kPa and P = 150 kPa. If the stagnation temperature is 400 K, estimate the freestream Mach number and velocity.
An airplane is flying at a standard altitude of 10,000 ft. A Pitot tube mounted at the nose measures a pressure of 2220 lb/ft2. The airplane is flying at a high subsonic speed, faster than 300 mph. The flow should be considered compressible. Calculate the velocity of the airplane.

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Air flows in the duct shown in Figure. The first shock, which turns the flow 15°, is observed to form at a 40° angle. The flow is known to be supersonic in regions 1 and 2 and subsonic in region 3. (a) Determine M3 and B. (b) Determine the pressure ratios P3/P1 and po3/P01.