MAE155A_HW2A_soln

# MAE155A_HW2A_soln - MAE 155A Aerospace Engineering Design I...

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MAE 155A Aerospace Engineering Design I Winter 2010 Homework #2A (Aircraft Design) DUE DATE: Thursday, 28 JAN 2010 Problem #1: The NACA 65(216)-415 airfoil (Raymer, page 792) is being considered for design of an executive jet. The wing area is 600 ft 2 and approximate cruise weight is 20,000 lb. Assume the aspect ratio is large enough that the wing aerodynamic characteristics can be approximated by the airfoil section characteristics. (a) What will be the wing angle-of-attack if the airplane cruises at M = 0.4 and altitude = 20,000 ft? (b) What is the (no flaps) stall speed at sea level? Problem #2: The (recently retired) Lockheed S-3 performs the same mission as the ASW design example considered in class. Create a performance constraint plot, T/W versus W/S, that considers the following stall speed and rate-of-climb requirements: stall speed < 97 nmi/hr at sea level rate-of-climb > 5,120 ft/min at sea level, with airspeed of 350 nmi/hr Compare the performance constraint lines to the actual S-3

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## This note was uploaded on 08/02/2010 for the course MAE 155a taught by Professor Staff during the Fall '08 term at UCSD.

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MAE155A_HW2A_soln - MAE 155A Aerospace Engineering Design I...

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