Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 11, Problem 11.7P
To determine
The critical Mach number at point A is
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A high-flying jet cruising at 3000km/hr displays a Mach Number of 3.2. What is the speed of sound and the temperature of the air at that altitude?
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A high-speed subsonic private jet is flying at a pressure
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measures a pressure of 4.21 x 104 N/m².
• Calculate the Mach number at which the airplane is flying.
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Chapter 11 Solutions
Fundamentals of Aerodynamics
Ch. 11 - Consider a subsonic compressible flow in cartesian...Ch. 11 - Using the Prandtl-Glauert rule, calculate the lift...Ch. 11 - Under low-speed incompressible flow conditions,...Ch. 11 - In low-speed incompressible flow, the peak...Ch. 11 - For a given airfoil, the critical Mach number is...Ch. 11 - Consider an airfoil in a Mach 0.5 freestream. At a...Ch. 11 - Prob. 11.7PCh. 11 - Consider the flow over a circular cylinder; the...Ch. 11 - In Problem 11.8, the critical Mach number for a...
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- 52. Calculate the air temperature at first level for an airplane flies at two altitudes (v1 = 745 m-s, µ2 =D33°, the Mach no. difference is 0.24).arrow_forward01: The velocity, pressure, and temperature at a certain point in a steady air flow, are 600 m/s, 70 kPa, and 5 °C, respectively. If the pressure at some other point in the flow is 30 kPa, find the Mach number, temperature, and velocity that exist at this second point. Assume that the flow is isentropic and one-dimensional.arrow_forwardA flow with Mach number M1 = 2 and pressure p1 = 1 atm is turned away from itself twice,first through an angle of 10 deg and then through a second angle of 20 deg. Compute the Machnumber and the static pressure downstream of the second turn. Then, suppose that the original flow(M1 = 2 and p1 = 1 atm) is turned away from itself through a single turn of 30 deg. Compute theMach number and static pressure downstream of this turn, and show that the values are the sameas for the first flow with two turns totaling 30 deg.3arrow_forward
- Air with pressure, temperature and density corresponding to a standard sea level condition is allowed to expand isentropically to a state where pressure is 2050 lb/in^2 and the corresponding velocity is 300 ft/s. Calculate the Mach the second statearrow_forward5. Typical cruising speeds and altitudes for three commercial aircraft are: Dash 8: Cruising speed: 500 km/h at an altitude of 4570 m. Boeing 747: Cruising speed: 978 km/h at an altitude of 9150 m. Concorde: Cruising speed: 2340 km/h at an altitude of 16 600 m. Find the Mach number of these three aircraft when flying at these cruise conditions. Use the properties of the standard atmosphere discussed in the previous problem.arrow_forwardWhat is the Mach number of an airflow with a velocity of 2000m/s, at 2,000 ft altitude?arrow_forward
- derive an expression for the mass flowrate of air for a C-D nozzle arrangement operating in choked flow conditions. Hint: start with the fact that: mmax = p* A*V * show all your steps. upload your answer here.arrow_forwardExample 2. A high-speed AC 130 gunship is flying at a pressure altitude of 10 km. A Pitot tube on the wingtip measures a pressure of 4.24 x 10ª N/m2. Calculate the Mach number at which the aircraft is flying. Solution: Solving for P1 at an altitude of 10000 m, we get 2.65 x 104 N/m2 k-1 1.4-1 Po k 4.24 x 104) 1.4 M? k – 1 - 1 - 1 1.4 – 1 2.65 x 104 M? = 0.719 M1 = 0.848arrow_forward3.2. 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 temperaturearrow_forward
- Using the Image below solve the following two questions, AND ONLY SOLVE FOR i and iii a.Determine The total pressure loss in the final state, after the 20 degree turn, for i and iii. (I'd also like to confirm for ii that the total pressure loss is 0?) b.Determine the Mach number in the final state. For which geometry is this highest? ( For ii it is 2.12)arrow_forward3. The NASA X-43 flies at a Mach number of 9.4 at an altitude of 30,000 m, where thepressure is 1171.8 Pa and the temperature is 226 K. If a supersonic wind tunnel isdesigned to reproduce these conditions, calculate the following:(a) The velocity (m/s), total/stagnation temperature (K), and total/stagnation pres-sure (kPa) in the test section.(b) The velocity (m/s), total temperature (K), and total pressure (kPa) behind thenormal shock formed in front of a blunt surface in the test section.(c) The change in entropy across this normal shock.arrow_forwarda low-speed aircraft is flying at an altitude of 1500 meters. The outside air temperature measures 300 R and a pitot tube mounted on the wing tip measures a pressure of 1750 psf. What is the true velocity and the equivalent airspeed? What is the dynamic pressure and the total pressure?arrow_forward
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