Is it possible to mix multiple airfoil profiles for an aircraft wing? If so, then why.
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- What is the strength of the vortex sheet ? As we placed a vortex sheet along the airfoil, how to limit the strength distribution ?a)What is the impact of increasing Reynolds number on skin friction and pressure drags over an airfoil? What can be happened for separation in this case? b) What is an adverse pressure gradient and where does it occur on an airfoil (show that on a sketch)? c) Why lift-to-drag ratio is an important parameter for an aircraft? d)How can changing in altitude affect the aircraft power required, PR? Show thatmathematically and graphically?From Table the drag coefficient of a wide plate normalto a stream is approximately 2.0. Let the stream conditionsbe U∞ and p∞. If the average pressure on the front of theplate is approximately equal to the free-stream stagnationpressure, what is the average pressure on the rear?
- discuss various designs of winglets to reduce induced drag.A commercial airplane has a total mass of 70,000 kg and a wing planform area of 150 m2. The plane has a cruising speed of 558 km/h and a cruising altitude of 12,000 m, where the air density is 0.312 kg/m3. The plane has double-slotted flaps for use during takeoff and landing, but it cruises with all flaps retracted. Assuming the lift and the drag characteristics of the wings can be approximated by NACA 23012 , determine (a) the minimum safe speed for takeoff and landing with and without extending the flaps, (b) the angle of attack to cruise steadily at the cruising altitude, and (c) the power that needs to be supplied to provide enough thrust to overcome wing drag.How does a winglet on the wing tip reduce induced drag? Which drag is higher if an aircraft is flying at 100knts and the L/Dmax is 120knts? How do you know this?
- The drag of an airfoil (Fig.) increases considerably ifyou turn the sharp edge around 180° to face the stream. Canyou explain this?What is the Effect of wing plan form (taper ratio and wing twist) and aspect ratio(AR) on the Induced drag coefficient, ?Name some applications in which a large drag is desired.
- Consider an NACA 2412 airfoil with a 2-m chord in an airstream with avelocity of 50 m/s at standard sea level conditions. If the lift per unit spanis 1353 N/m, what is the angle of attack?Air is flowing past a symmetrical airfoil at an angle of attack of 5°. Is the (a) lift and (b) drag acting on the airfoil zero or nonzero?An airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The airfoil has an aspect ratio of 10 with a span of 36 m. Using the airfoil data as in Fig. 3, determine the lift and drag forces. Then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2.