1. The flow is considered compressible when the value of Mach number is....(A) greater than unity (B) greater or equal to 0.3 (C) greater than 0.5 (D) less than 0.32. In c-d nozzle, when dA/dV is positive, then the flow is....(A) subsonic(B) sonic (C) supersonic (D) incompressible3. Along the adiabatic duct, the...... remains constant.(A) stagnation pressure (B) static pressure (C) static temperature (D) stagnation temperature4. Across the normal shock wave, the gas velocity ......(A) decreases↓(B) increases ↑(C) remains constant(D) varies randomlyv2(C)2Cp(D) PV²5. The dynamic temperature can be calculated from.....(A):M²2Cp(B) -M²B6. A supersonic flow with 38° oblique shock angle passes over a concave corner of angle 0=20°. Then,the free stream Mach number M₁ is....(A) 2(B) 57. Across the expansion waves, the ..... remains constant.(A) Mach number(B) stagnation pressure(C) 3(C) gas velocity(D) 4(D) temperature.(D) Pe=08. The maximal thrust of the rocket can be obtained when the exit pressure (Pe) is ....(A) Pe=Pa(B) Pe>Pa9. In turbojet engine, the water can be injected.....(A) before the compressor(C) Pe

The flow is considered compressible when the value of Mach number is (A) greater than unity. This is…

Answered: 1. The flow is considered compressible…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

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3:34 ull Q3.pdf Q1) Air at mach number 2 , pressure 0.5* 10° N/m² and a temperature of 0 °C , over a wedge and generation of an oblique shock wave 40° . determine : 1. Static pressure and temperature downstream the shock. 2. The mach number of the flow downstream the shock. 3. The wedge angle. *********** Q2) As shown in figure (1) A mach number 2.4 air stream at oblique shock angle of (B1-2 =30°) of incident shock with turning angle (0=10°). determine : 1. the mach number of the flow upstream the reflected shock. 2. the mach number of the flow downstream the reflected shock. M2 M3 Figure (1)
Please answer c A supersonic converging-diverging nozzle is near the exit of a turbojet engine. Its cross-section is circular. The gas has the properties of air, and the flow is isentropic. At the throat location (the minimum area) the air flow is choked (is Mach one) and the throat has diameter of 20 cm.
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Compressible Flow and Propulsion 1. Determine the speed of sound in Argon at 120 °C. Molecular weight of Argon = 40 kg/kmol and y= 1.667. (Ro = 8314.5 J/kmol K) %3D [Ans. 369 m/s] 2. Calculate the Mach number corresponding to the following speeds at an am temperature of 15 °C. Rair = 287 J kg*K, 1 mph = 0.447 ms?. ent (a) National speed limit of 70 mph [Ans. 0.09] (b) A top speed of 230 mph attained by a Formula driver. [Ans. 0.3] 3. Calculate the speed of an aircraft cruising in 20°C air where the angle of the zone of silence is a. 10° to the direction of travel. [1946ms) b. 20° to the direction of travel. [943ms] c. 80° to the direction of travel. [60ms] d. What is the maximum expected angle for M = 1? 4. Calculate the speed of sound during the flight of an aircraft for the two conditions (a) when it is at a cruising altitude of 10,000 m and the outside temperature is-60 °C. (b) when it lands in a desert city at a temperature of 45 °C (c) If the Mach number during cruising condition…
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For supersonic and hypersonic wind tunnels, a diffuser efficiency, ηD,can be defined as the ratio of the total pressures at the diffuser exit andnozzle reservoir, divided by the total pressure ratio across a normal shockat the test-section Mach number. This is a measure of the efficiency ofthe diffuser relative to normal shock pressure recovery. Consider asupersonic wind tunnel designed for a test-section Mach number of 3.0which exhausts directly to the atmosphere. The diffuser efficiency is 1.2.Calculate the minimum reservoir pressure necessary for running thetunnel.
1.AB

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