# hw4 - 16.100 Homework Assignment # 4 Due: Monday, October 3...

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16.100 Homework Assignment # 4 Due: Monday, October 3 at 9am Reading Assignment Handout “Thin Airfoil Theory Summary” Anderson, 3 rd edition: Chapter 4 Section 4.1 – 4.9 Note: I did not give a targeted reading assignment for the problems, because essentially all of the reading is useful for all of the problems. Problem #1 (30%) In this problem, we will consider the aerodynamic impact of leading and trailing edge flaps on an airfoil using thin airfoil theory. To be specific, we will consider the following camberline: x c = 01 . x c = 09 . α V η 0 1 where the leading and trailing edge flap deflection angles (defined positive downwards) are 0 and 1 , respectively. In the following problems, use thin airfoil theory and assume small angles throughout. (a) Calculate the derivative of the lift coefficient with respect to the leading edge flap deflection, ∂∂ c l / 0 . (b) Calculate the derivative of the lift coefficient with respect to the trailing edge flap deflection, c l / 1 . (c) Show that trailing edge flap has a significantly greater impact on the lift coefficient than the leading edge flap.

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Problem #2 (40%)
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## This note was uploaded on 11/06/2011 for the course AERO 100 taught by Professor Willcox during the Fall '03 term at MIT.

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hw4 - 16.100 Homework Assignment # 4 Due: Monday, October 3...

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