Questions from Fundamentals of Aerodynamics

Q: The question is often asked: Can an airfoil fly upside-

The question is often asked: Can an airfoil fly upside-down? To answer this, make the following calculation. Consider a positively cambered airfoil with a zero-lift angle of 3◦. The lift slope is 0.1...

Q: The airfoil section of the wing of the British Spitfire of World

The airfoil section of the wing of the British Spitfire of World War II fame (see Figure 5.19) is an NACA 2213 at the wing root, tapering to an NACA 2205 at the wing tip. The root chord is 8.33 ft. Th...

Q: For the conditions given in Problem 4.15, a more

For the conditions given in Problem 4.15, a more reasonable calculation of the skin friction coefficient would be to assume an initially laminar boundary layer starting at the leading edge, and then t...

Q: A U-tube mercury manometer is used to measure the pressure

A U-tube mercury manometer is used to measure the pressure at a point on the wing of a wind-tunnel model. One side of the manometer is connected to the model, and the other side is open to the atmosph...

Q: Consider an NACA 2412 airfoil with a 2-m chord in

Consider an NACA 2412 airfoil with a 2-m chord in an airstream with a velocity of 50 m/s at standard sea level conditions. If the lift per unit span is 1353 N/m, what is the angle of attack?

Q: Starting with the definition of circulation, derive Kelvin’s circulation theorem,

Starting with the definition of circulation, derive Kelvin’s circulation theorem, Equation (4.11).

Q: Starting with Equation (4.35), derive Equation (4

Starting with Equation (4.35), derive Equation (4.36).

Q: Consider a thin, symmetric airfoil at 1.5◦ angle

Consider a thin, symmetric airfoil at 1.5◦ angle of attack. From the results of thin airfoil theory, calculate the lift coefficient and the moment coefficient about the leading edge.

Q: The NACA 4412 airfoil has a mean camber line given by

The NACA 4412 airfoil has a mean camber line given by Using thin airfoil theory, calculate (a) αL=0 (b) cl when α = 3◦

Q: For the airfoil given in Problem 4.6, calculate cm

For the airfoil given in Problem 4.6, calculate cm,c/4 and xcp/c when α = 3◦.