Questions from Fundamentals of Aerodynamics

Q: Using the results of linearized theory, calculate the lift and wave

Using the results of linearized theory, calculate the lift and wave-drag coefficients for an infinitely thin flat plate in a Mach 2.6 freestream at angles of attack of (a) α=5◦ (b) α=15◦ (c) α=30◦ C...

Q: For the conditions of Problem 12.1, calculate the pressures

For the conditions of Problem 12.1, calculate the pressures (in the form of p/ p∞) on the top and bottom surfaces of the flat plate, using linearized theory. Compare these approximate results with tho...

Q: Consider a diamond-wedge airfoil such as shown in Figure 9

Consider a diamond-wedge airfoil such as shown in Figure 9.37, with a half-angle ε=10◦. The airfoil is at an angle of attack α=15◦ to a Mach 3 freestream. Using linear theory, calculate the lift and w...

Q: Equation (12.24), from linear supersonic theory, predicts

Equation (12.24), from linear supersonic theory, predicts that cd for a flat plate decreases as M∞ increases? Does this mean that the drag force itself decreases as M∞ increases? To answer this questi...

Q: Consider a flat plate at an angle of attack in an inviscid

Consider a flat plate at an angle of attack in an inviscid supersonic flow. From linear theory, what is the value of the maximum lift-to-drag ratio, and at what angle of attack does it occur?

Q: Consider a flat plate at an angle of attack in a viscous

Consider a flat plate at an angle of attack in a viscous supersonic flow; i.e., there is both skin friction drag and wave drag on the plate. Use linear theory for the lift and wave-drag coefficients....

Q: Using the same flight conditions and the same value of the skin

Using the same flight conditions and the same value of the skin-friction coefficient from Example 12.3, and the results of Problem 12.6, calculate the maximum lift-to-drag ratio of the flat plate that...

Q: The result from Problem 12.6 demonstrates that maximum lift-

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 g...

Q: Assuming the velocity field given in Problem 2.6 pertains to

Assuming the velocity field given in Problem 2.6 pertains to an incompressible flow, calculate the stream function and velocity potential. Using your results, show that lines of constant φ are perpend...

Q: Consider two points in a supersonic flow. These points are located

Consider two points in a supersonic flow. These points are located in a cartesian coordinate system at (x1, y1) = (0, 0.0684) and (x2, y2) = (0.0121, 0), where the units are meters. At point (x1, y1):...