Questions from Fundamentals of Aerodynamics

Q: A Pitot tube on an airplane flying at standard sea level reads

A Pitot tube on an airplane flying at standard sea level reads 1.07 *105 N/m2. What is the velocity of the airplane?

Q: At a given point on the surface of the wing of the

At a given point on the surface of the wing of the airplane in Problem 3.6, the flow velocity is 130 m/s. Calculate the pressure coefficient at this point.

Q: Consider a Lear jet flying at a velocity of 250 m/

Consider a Lear jet flying at a velocity of 250 m/s at an altitude of 10 km, where the density and temperature are 0.414 kg/m3 and 223 K, respectively. Consider also a one-fifth scale model of the Lea...

Q: Consider a uniform flow with velocity V∞. Show that this flow

Consider a uniform flow with velocity V∞. Show that this flow is a physically possible incompressible flow and that it is irrotational.

Q: Show that a source flow is a physically possible incompressible flow everywhere

Show that a source flow is a physically possible incompressible flow everywhere except at the origin. Also show that it is irrotational everywhere.

Q: Consider the data for the NACA 2412 airfoil given in Figure 4

Consider the data for the NACA 2412 airfoil given in Figure 4.10. Calculate the lift and moment about the quarter chord (per unit span) for this airfoil when the angle of attack is 4◦ and the freestre...

Q: For the NACA 2412 airfoil, the lift coefficient and moment coefficient

For the NACA 2412 airfoil, the lift coefficient and moment coefficient about the quarter-chord at -6◦ angle of attack are -0.39 and -0.045, respectively. At 4◦ angle of attack, these coefficients are...

Q: Consider again the NACA 2412 airfoil discussed in Problem 4.10

Consider again the NACA 2412 airfoil discussed in Problem 4.10. The airfoil is flying at a velocity of 60 m/s at a standard altitude of 3 km (see Appendix D). The chord length of the airfoil is 2 m. C...

Q: For the airfoil in Problem 4.11, calculate the value

For the airfoil in Problem 4.11, calculate the value of the circulation around the airfoil.

Q: In Section 3.15 we studied the case of the lifting

In Section 3.15 we studied the case of the lifting flow over a circular cylinder. In real life, a rotating cylinder in a flow will produce lift; such real flow fields are shown in the photographs in F...