In reality, the boundary layer on the airfoil discussed in prob. 5.37 is neither fully laminar nor fully turbulent. the boundary layer starts out as laminar, and then transitions to turbulent at some point downstream of the leading edge (see the discussion in sec. 4.19). assume that the critical reynolds number for transition is 650,000. calculate the skin friction drag coeffi cient on the naca 2415 airfoil, and compare your result with the experimental section drag coeffi cient in app. d. note: you will fi nd from the answer to this problem that 86 percent of the airfoil section drag coeffi cient is due to skin friction and 14 percent due to pressure drag from fl ow separation. comparing this answer with the result of prob. 5.36 , which pertains to a thinner airfoil, we fi nd that the pressure drag is a higher percentage for the thicker airfoil. however, for airfoils in general, the pressure drag is still a small percentage of the total drag. this drag breakdown is somewhat typical for airfoils at small angles of attack. by intent, the streamlined shape of airfoils results in small pressure drag, typically on the order of 15 percent of the total drag.
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Physics, 22.06.2019 01:20
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Each line (unit) on the horizontal axis represents: 5 years 10 years 20 years all of the above
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Physics, 23.06.2019 07:00
A55-kg pilot flies a jet trainer in a half vertical loop of 1200-m radius so that the speed of the trainer decreases at a constant rate. knowing that the plane has a speed of 550 km/h at point a, and the pilot experiences weightlessness at point c (i.e., the normal force from the seat bottom is zero), determine (a) the deceleration of the plane, (b) the force exerted on her by the seat of the trainer when the trainer is at point b.
Answers: 2
In reality, the boundary layer on the airfoil discussed in prob. 5.37 is neither fully laminar nor f...
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