Beginner's
Guide to Aerodynamics Drag Equation - Level 1 Answers
A = 1/2h(b1 + b2) = 1/2 x 76.48(25.3 + 48.9) = 2834.44 ft2 for one wing B. The thrust of the aircraft is 120,000 pounds and the air density is .00048 slugs/cu.ft. The current cruising speed is 450 mph and we need to determine the drag coefficient of the aircraft. Find the Cd. (Hint: you may want to convert the original equation first)Cd = 2D/(r x V2 x A) = 2(120,000)/(.00048)(450)2(5668.88) = .436
C. Weather conditions force the aircraft to descend to a level where the air density is .00076 slugs/cu.ft. The engine thrust increases to 250,000 pounds. At the new cruising altitude, what is the speed of the aircraft? (Hint: once again, you may want to convert the equation first)
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