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 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.

for mach angle at sea level , T = 288.15 - 6.5 x 0 = 288.15 and a= 340.26 m/s but there is no…

Answered: Problem 3. A supersonic airplane is…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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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 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 approximating temperature variation)
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.
5. At 30000ft, estimate the magnitude of transonic drag rise. Using this estimate, calculate the maximum velocity of the airplane at this altitude. Assume drag-divergence Mach number of 0.82 and d(D/D₁)/dM = 14.3 where D₁=1750lb is drag at Mach number 0.9 and D₂ = 4250lb at Mach number 1. 6 Estimate maximum range at 30000€ Also calculate the flight speed to obtain this
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?
Consider the Gulfstream IV flying at Mach = 0.8 at an altitude with atmospheric pressure of 33,283.40-Pa. Calculate thrust required assuming a weight of 73,000-lb. Airplane data: S = 950 ft2, AR = 5.92, ?Do = 0.015, and K = 0.08. The thrust required. (in lbf)
(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?
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)?
Problem 4. High-speed aircraft use "air data computers" to compute air speed from Pitot-static tube measurements of the stagnation pressure and static pressure. (a) Plot the percent error in computing the Mach number assuming incompressibility (thus, using the Bernoulli equation) versus actual Mach number for Ma = 0.1 to Ma=0.9. (b) For an aircraft cruising at an altitude of z = 12 km, plot the speed calculated assuming incompressible flow and accounting for compressibility versus actual Mach number for Ma = 0.1 to Ma = 0.9.
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.
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)

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