Q: Compare the results of Problems 4.6 and 4.7
Compare the results of Problems 4.6 and 4.7 with experimental data for the NACA 4412 airfoil, and note the percentage difference between theory and experiment. (Hint: A good source of experimental air...
See AnswerQ: Starting with Equations (4.35) and (4.
Starting with Equations (4.35) and (4.43), derive Equation (4.62).
See AnswerQ: Consider a vortex filament of strength Г in the shape of a
Consider a vortex filament of strength Г in the shape of a closed circular loop of radius R. Obtain an expression for the velocity induced at the center of the loop in terms of Г and R.
See AnswerQ: If the elliptical wing of the Spitfire in Problem 5.9
If the elliptical wing of the Spitfire in Problem 5.9 were replaced by a tapered wing with a taper ratio of 0.4, everything else remaining the same, calculate the induced drag coefficient. Compare thi...
See AnswerQ: The German Zeppelins of World War I were dirigibles with the following
The German Zeppelins of World War I were dirigibles with the following typical characteristics: volume =15,000 m3 and maximum diameter= 14.0 m. Consider a Zeppelin flying at a velocity of 30 m/s at a...
See AnswerQ: Consider the Spitfire in Problem 5.9 on its landing approach
Consider the Spitfire in Problem 5.9 on its landing approach at sea level with a landing velocity of 70 mi/h. Calculate the induced drag coefficient for this low-speed case. Compare your result with t...
See AnswerQ: Consider the same vortex filament as in Problem 5.1.
Consider the same vortex filament as in Problem 5.1. Consider also a straight line through the center of the loop, perpendicular to the plane of the loop. Let A be the distance along this line, measur...
See AnswerQ: The measured lift slope for the NACA 23012 airfoil is 0.
The measured lift slope for the NACA 23012 airfoil is 0.1080 degree−1, and αL=0 = −1.3◦. Consider a finite wing using this airfoil, with AR = 8 and taper ratio = 0.8. Assume that δ = τ . Calculate the...
See AnswerQ: The Piper Cherokee (a light, single-engine general aviation
The Piper Cherokee (a light, single-engine general aviation aircraft) has a wing area of 170 ft2 and a wing span of 32 ft. Its maximum gross weight is 2450 lb. The wing uses an NACA 65-415 airfoil, wh...
See AnswerQ: Consider the airplane and flight conditions given in Problem 5.4
Consider the airplane and flight conditions given in Problem 5.4. The span efficiency factor e for the complete airplane is generally much less than that for the finite wing alone. Assume e=0.64. Calc...
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