Q: Consider a finite wing with an aspect ratio of 6. Assume
Consider a finite wing with an aspect ratio of 6. Assume an elliptical lift distribution. The lift slope for the airfoil section is 0.1/degree. Calculate and compare the lift slopes for (a) a straigh...
See AnswerQ: Repeat Problem 5.6, except for a lower aspect ratio
Repeat Problem 5.6, except for a lower aspect ratio of 3. From a comparison of the results from these two problems, draw some conclusions about the effect of wing sweep on the lift slope, and how the...
See AnswerQ: In Problem 1.19 we noted that the Wright brothers,
In Problem 1.19 we noted that the Wright brothers, in the design of their 1900 and 1901 gliders, used aerodynamic data from the Lilienthal table given in Figure 1.65. They chose a design angle of atta...
See AnswerQ: Consider the Supermarine Spitfire shown in Figure 5.19. The
Consider the Supermarine Spitfire shown in Figure 5.19. The first version of the Spitfire was the Mk I, which first flew in 1936. Its maximum velocity is 362 mi/h at an altitude of 18,500 ft. Its weig...
See AnswerQ: Prove that three-dimensional source flow is irrotational.
Prove that three-dimensional source flow is irrotational.
See AnswerQ: Consider a circular cylinder in a hypersonic flow, with its axis
Consider a circular cylinder in a hypersonic flow, with its axis perpendicular to the flow. Let φ be the angle measured between radii drawn to the leading edge (the stagnation point) and to any arbitr...
See AnswerQ: Prove that three-dimensional source flow is a physically possible incompressible
Prove that three-dimensional source flow is a physically possible incompressible flow.
See AnswerQ: A sphere and a circular cylinder (with its axis perpendicular to
A sphere and a circular cylinder (with its axis perpendicular to the flow) are mounted in the same freestream. A pressure tap exists at the top of the sphere, and this is connected via a tube to one s...
See AnswerQ: The temperature and pressure at the stagnation point of a high-
The temperature and pressure at the stagnation point of a high-speed missile are 934 ◦R and 7.8 atm, respectively. Calculate the density at this point.
See AnswerQ: Calculate the percentage error obtained if Problem 7.9 is solved
Calculate the percentage error obtained if Problem 7.9 is solved using (incorrectly) the incompressible Bernoulli equation.
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