Problem 3. A supersonic airplane is cruising at a Mach number of Ma = 2.2 at an altitude of H = 17 km on astandard day. (a) Calculate the speed, V, of the airplane. (b) Calculate the Mach angle using the temperature atz = H and at sea level. (c) Estimate how long after the aircraft passes directly above a ground observer wouldhear the sound created by the airplane. (HINT: You can use the average height to estimate the Mach angle.)Recall that for the U.S. Standard Atmosphere, the temperature distribution below H is given by: T = Tom zfor 011 km where To = 288.15 K and m = -6.5 K/km; T = 216.65 K for 11 ≤ z < 20.1 km.Problem 3. (a) 649 m/s, (b) 27.0 deg., 31.6 deg., (c) 46.6 s or 48.0 s (depending on method for approximatingtemperature variation)

Answered: Image /qna-images/answer/d8c43dd1-4160-46bb-81fc-9fb5370de379.jpg

Answered: Problem 3. A supersonic airplane is…

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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Problem 3. A supersonic airplane is cruising at a Mach number of Ma = 2.2 at an altitude of H = 17 km on a standard day. (a) Calculate the speed, V, of the airplane. (b) Calculate the Mach angle using the temperature at z = H and at sea level. (c) Estimate how long after the aircraft passes directly above a ground observer would hear the sound created by the airplane. (HINT: You can use the average height to estimate the Mach angle.) Recall that for the U.S. Standard Atmosphere, the temperature distribution below H is given by: T = Tom z for 0 ≤ x ≤ 11 km where To = 288.15 K and m = −6.5 K/km; T = 216.65 K for 11 ≤ z < 20.1 km.
A jet transport is flying at a standard altitude of 30,000 feet with a velocity of 550 miles per hour. What is the Mach number?
Problem 5. A Boeing 747 cruises at a Mach number of Ma = 0.87 at an altitude of z = 13 km on a standard day. A window in the cockpit is located where the external flow outside the window is at a Mach number of Ma = 0.2 relative to the plane surface (just outside the boundary layer). The cabin is pressurized to an equivalent altitude of z = 2.5 km for a standard atmosphere. (a) Estimate the pressure difference across the window and specify the direction of the net pressure force. (b) Sketch the stagnation pressure, static pressures, and critical pressure on a T-s diagram.
A P-51 Mustang is traveling at 24000 ft altitude. The inlet air temperature is 5 degrees C. Calculate the speed of sound (in m/s) in the intake port. If the average Mach Number of the intake port is 0.46, what is the speed of the intake airflow?
(a) The maximum speed achieved by the X-15A-2 rocket-powered research craft was 6630 ft/s at 99,000 ft. Assuming standard day conditions, whatwas its Mach number?(b) An SR-71 is traveling at Mach 3.2 in standard day 80,000-ft conditions.What is its velocity in nautical miles per hour?
The Pitot tube on a supersonic aircraft (see the Video) cruising at an altitude of 25000 ft senses a stagnation pressure of 15.0 psia. If the atmosphere is considered standard, determine (a) the Mach number of the aircraft, (b) the airspeed. A shock wave is present just upstream of the probe impact hole. (a) Ma = (b) V= ft/s
For a projectile traveling at 800 mph through air at 50 °F and standard atmospheric pressure, what is the value of the Mach number?
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)?
An air tank with a nozzle, has a pressure of twice the standard sea level pressure and density of 2.45 kg/m³. Outside the converging-diverging nozzle, the pressure corresponds to an altitude of 3km and designed to have a mach number of 1.0 and 1.8 at the throat and exit, respectively. The area at the throat is 0.15 square meters. Calculate: a) the temperature and speed of sound in the tank. b) pressure and density at the throat c) mass flow rate at the exit.
3.2. At a given point in a supersonic wind tunnel, the pressure and temperature are 5 x 104 N/m and 200 K, respectively The total pressure at this point is 1 5 x 106 N/m? Calculate the local Mach number and total temperature
Consider the Gulfstream IV flying at Mach = 0.35. Calculate thrust required given an altitude of 30,000-ft, assuming weight of 73,000-lb. Airplane data: S = 950 ft2, AR = 5.92, ??? = 0.015, and K = 0.08 a. The thrust required at 30,000-ft. (in pounds)
Consider an airplane flying at a velocity of 250 m/s. Calculate its Mach number if it is flying at a standard altitude of (a) sea level, (b) 5 km, (c) 10 km.

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