FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
6th Edition
ISBN: 9781265141387
Author: Anderson
Publisher: MCG
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Chapter 11, Problem 11.7P
To determine
The critical Mach number at point A is
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On October 3, 1967, pilot William J. "Pete" Knight set a world record that still stands to this day for the fastest flight by a crewed, powered aircraft by flying the North American Aviation X-15 as fast as Mach 6.7 at an altitude of 102,000 ft above sea level. Mach number is the ratio of an object’s velocity to the local speed of sound. Using the table for atmospheric properties with respect to altitude, calculate the speed of sound at an altitude of 100,000 ft. What must have been the velocity of the X-15?
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Chapter 11 Solutions
FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
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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- A high-speed subsonic private jet is flying at a pressure altitude of 11 km. A Pitot tube on the wing tip measures a pressure of 4.21 x 104 N/m². • Calculate the Mach number at which the airplane is flying. • If the ambient air temperature is 225 K, calculate; • the true airspeed and • the calibrated airspeedarrow_forward52. 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_forward
- A 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_forwardAir 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_forward
- What is the Mach number of an airflow with a velocity of 2000m/s, at 2,000 ft altitude?arrow_forwardderive 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_forward
- 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 temperaturearrow_forwardUsing 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_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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