Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 12, Problem 12.8P
The result from Problem 12.6 demonstrates that maximum lift-to-drag ratio decreases as the Mach number increases. This is a fact of nature that progressively causes designers of supersonic airplanes grief as they strive toward aerodynamically efficient airplanes a higher supersonic Mach numbers. What physics is nature using against the airplane designer in this case, and how might the designer meet this challenge?
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Chapter 12 Solutions
Fundamentals of Aerodynamics
Ch. 12 - Using the results of linearized theory, calculate...Ch. 12 - For the conditions of Problem 12.1, calculate the...Ch. 12 - Consider a diamond-wedge airfoil such as shown in...Ch. 12 - Equation (12.24). from linear supersonic theory....Ch. 12 - Consider a flat plate at an angle of attack in an...Ch. 12 - Consider a flat plate at an angle of attack in a...Ch. 12 - Using the same flight conditions and the same...Ch. 12 - The result from Problem 12.6 demonstrates that...
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- In the test section of a supersonic wind tunnel, a Pitot tube in the flowreads a pressure of 1.13 atm. A static pressure measurement (from apressure tap on the sidewall of the test section) yields 0.1 atm. Calculatethe Mach number of the flow in the test section.arrow_forwardA uniform supersonic airflow traveling at Mach 2.0 passes over a wedge (Fig. 10E.1). An oblique shock, making an angle of 40° with the flow direction, is attached to the wedge under these flow conditions. If the static pressure and temperature in the uniform flow are, respectively, 20 kPa and −10 °C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle.arrow_forwardThe speed of a supersonic aircraft flying at an altitude of 1,100 meters corresponds to a Mach number of 2.5. Estimate the time elapsed, in seconds, between the instant the aircraft was directly over head of an observer and the instant the observer feels the disturbance due to the aircraft. Presume that the temperature at the given height is 280°K, with k = 1.4 and R = 2.87 J/kg·K, in determining the questions of the following three cases: A) When the observer is stationaryB) When the observer is moving in the direction of the aircraft at M = 0.5C) When the observer is moving in the opposite direction with M = 0.5.arrow_forward
- Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1 atm. Calculate the loss of total pressure across the shock wave when the upstream Mach number is (a) M1 = 2.5, and (b) M1 = 4.5. Compare these two results and comment on their implicationarrow_forwardConsider a rocket engine burning hydrogen and oxygen; the combustion chamber temperature and pressure are 3517 K and 26 atm, respectively. The molecular weight of the chemically reacting gas in the combustion chamber is 16, and y = 1.22. The pressure at the exit of the convergent-divergent rocket nozzle is 1.174 x10-2 atm. The area of the throat is 0.4 m2. Assuming a calorically perfect gas and isentropic flow, calculate: (a) the exit Mach number, (b) the exit velocity, (c) the mass flow through the nozzle, and (d) the area of the exitarrow_forwardFor a projectile traveling at 800 mph through air at 50 °F and standard atmospheric pressure, what is the value of the Mach number?arrow_forward
- A supersonic flow passes over a symmetrical wedge of semi-angle α = 10° . At the leading edge an attached shock of β = 30° is observed. Find: (a) The upstream Mach number. (b) The downstream Mach number. (c) The static pressure ratio across the shock.arrow_forwardConsider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are 5 atm and 500 K, respectively. If the Mach number at the nozzle exit is 3, calculate the exit pressure, temperature, and density.arrow_forwardA Pitot tube is inserted into an airflow where the static pressure is 1 atm. Calculate the flow Mach number when the Pitot tube measures (a) 1.276 atm, (b) 2.714 atm, (c) 12.06 atm.arrow_forward
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