The wing of a tactical support aircraft is approximately rectangular with a wingspan (the length perpendicular to the flow direction) of 16.5 m and a chord (the length parallel to the flow direction) of 2.75 m. The airplane is flying at standard sea level with a velocity of 250 ms¯¹. Assume the wing is approximated by a flat plate. Assume incompressible flow. Use μ = 1.789 x 10-5 kg/ms (a) If the flow is considered to be completely laminar, calculate the boundary layer thickness at the trailing edge and the total skin friction drag.

The wing of a tactical support aircraft is approximately rectangular with a wingspan (the length perpendicular to the flow direction) of 16.5 m and a chord (the length parallel to the flow direction) of 2.75 m. The airplane is flying at standard sea level with a velocity of 250 ms¯¹. Assume the wing is approximated by a flat plate. Assume incompressible flow. Use μ = 1.789 x 10-5 kg/ms (a) If the flow is considered to be completely laminar, calculate the boundary layer thickness at the trailing edge and the total skin friction drag.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

The wing of a tactical support aircraft is approximately rectangular with a wingspan (the length
perpendicular to the flow direction) of 16.5 m and a chord (the length parallel to the flow
direction) of 2.75 m. The airplane is flying at standard sea level with a velocity of 250 ms¯¹.
Assume the wing is approximated by a flat plate. Assume incompressible flow. Use μ =
1.789 x 10-5 kg/ms
(a) If the flow is considered to be completely laminar, calculate the boundary layer
thickness at the trailing edge and the total skin friction drag.

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Step 2: Finding Reynold's number at the trailing edge

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Step 3: Finding boundary layer thickness

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Step 4: Finding coefficient of drag

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Step 5: Finding total skin friction drag

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