Explanation Write the expression of lift force generated by wings at sea level. L sea level = 1 2 C L , sea level ρ sea level U sea level 2 A (I) Here, the lift coefficient at sea level is C L , sea level , the density of air at sea level is ρ sea level , the velocity of wings at sea level is U sea level and the cross sectional area of the wings is A . Write the expression of lift force generated by wings at the altitude of 10 , 000 m . L 10 , 000 m = 1 2 C L , 10 , 000 m ρ 10 , 000 m U 10 , 000 m 2 A (II) Here, the lift coefficient at the altitude of 10 , 000 m is C L , 10 , 000 m , the density of air at the altitude of 10 , 000 m is ρ 10 , 000 m , the velocity of wings at the altitude of 10 , 000 m is U 10 , 000 m and the cross sectional area of the wings is A . Equate the value of lift force at sea level and lift force at the altitude of 10 , 000 m . L sea level = L 10 , 000 m (III) Substitute 1 2 C L , sea level ρ sea level U sea level 2 A for L sea level and 1 2 C L , 10 , 000 m ρ 10 , 000 m U 10 , 000 m 2 A for L 10 , 000 m in Equation (III). 1 2 C L , sea level ρ sea level U sea level 2 A = 1 2 C L , 10 , 000 m ρ 10 , 000 m U 10 , 000 m 2 A C L , sea level ρ sea level U sea level 2 = C L , 10 , 000 m ρ 10 , 000 m U 10 , 000 m 2 (IV) Consider, the lift coefficient at sea level is same as the lift coefficient at the altitude of 10 , 000 m

Munson, Young and Okiishi's Fundamentals of Fluid Mechanics, Binder Ready Version

8th Edition

ISBN: 9781119080701

Author: Philip M. Gerhart, Andrew L. Gerhart, John I. Hochstein

Publisher: WILEY

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Question

Chapter 9.4, Problem 107P

To determine

The velocity of the wings at the altitude of 10,000 m.

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Chapter 9.4, Problem 106P

Chapter 9.4, Problem 108P

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Munson, Young and Okiishi's Fundamentals of Fluid Mechanics, Binder Ready Version

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