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Fox And Mcdonald's Introduction To Fluid Mechanics
9th Edition
ISBN: 9781118921876
Author: Pritchard, Philip J.; Leylegian, John C.; Bhaskaran, Rajesh
Publisher: WILEY
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Textbook Question
Chapter 12, Problem 90P
A supersonic aircraft cruises at M = 2.2 at 12 km altitude. A pitot tube is used to sense pressure for calculating air speed. A normal shock stands in front of the tube. Evaluate the local isentropic stagnation conditions in front of the shock. Estimate the stagnation pressure sensed by the pitot tube. Show static and stagnation state points and the process path on a Ts diagram.
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Students have asked these similar questions
The instrument fairing on an aircraft is shown below, consisting of a forward ramp at30◦, a horizontal section, and a rear ramp at 25◦. During a flight in air at Mach 5.5,the static pressure is 42.6 kPa and the static temperature is 250 K. An oblique shockforms at the turn of the forward ramp, two expansion fans form at the front and rear ofthe horizontal section, and a second oblique shock forms at the turn of the rear ramp.
(a) Calculate the Mach numbers and pressures at regions 2, 3, 4, and 5.
(b) Determine stagnation pressure ratio p05/p01.
(c) Tabulate the angles of all oblique shocks waves leading/trailing expansion waves relative to horizontal (not relative to flow angle).
Gamma = 1.4, R=287 J/kgK
PLEASE SHOW ALL WORK
Q6: Air following through constant area duct
encounters stationary shock as shown in figure.
Find the Mach number, temperature, pressure,
stagnation pressure, stagnation temperature and
velocity after the shock. Ans.: M2 = 0.6746, T2 =
344 K, p2 = 137 kPa, To = 375 K, po = 186 kPa.
V1=500 m/s
P;=50 kPa
1-250 K
→ (1) | (2)
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
Chapter 12 Solutions
Fox And Mcdonald's Introduction To Fluid Mechanics
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