Questions from Fundamentals of Aerodynamics

Q: Consider an NACA 2412 airfoil (the meaning of the number designations

Consider an NACA 2412 airfoil (the meaning of the number designations for standard NACA airfoil shapes is discussed in Chapter 4). The following is a tabulation of the lift, drag, and moment coefficie...

Q: Consider a light, single-engine, propeller-driven airplane

Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylane. The airplane weight is 2950 lb and the wing reference area is 174 ft2. The drag coefficient of the airplane CD i...

Q: Derive the Rayleigh Pitot tube formula, Equation (8.80

Derive the Rayleigh Pitot tube formula, Equation (8.80).

Q: On March 16, 1990, an Air Force SR-71

On March 16, 1990, an Air Force SR-71 set a new continental speed record, averaging a velocity of 2112 mi/h at an altitude of 80,000 ft. Calculate the temperature (in degrees Fahrenheit) at a stagnati...

Q: In the test section of a supersonic wind tunnel, a Pitot

In the test section of a supersonic wind tunnel, a Pitot tube in the flow reads a pressure of 1.13 atm. A static pressure measurement (from a pressure tap on the sidewall of the test section) yields 0...

Q: When the Apollo command module returned to earth from the moon,

When the Apollo command module returned to earth from the moon, it entered the earth’s atmosphere at a Mach number of 36. Using the results from the present chapter for a calorically perfect gas with...

Q: The stagnation temperature on the Apollo vehicle at Mach 36 as it

The stagnation temperature on the Apollo vehicle at Mach 36 as it entered the atmosphere was 11,000 K, a much different value than predicted in Problem 8.17 for the case of a calorically perfect gas w...

Q: Prove that the total pressure is constant throughout an isentropic flow.

Prove that the total pressure is constant throughout an isentropic flow.

Q: The temperature in the reservoir of a supersonic wind tunnel is 519

The temperature in the reservoir of a supersonic wind tunnel is 519 ◦R. In the test section, the flow velocity is 1385 ft/s. Calculate the test-section Mach number. Assume the tunnel flow is adiabatic...

Q: At a given point in a flow, T=300 K

At a given point in a flow, T=300 K, p=1.2 atm, and V=250 m/s. At this point, calculate the corresponding values of p0, T0, p∗, T ∗, and M ∗.