Problem 2 A Beechcraft Bonanza wing has the following dimensions: - chord = 1.4 m; - span (wing tip to wing tip) = 7m and - wing is roughly rectangular in shape. This plane is flying at 30 m/sec under standard sea level conditions. Model this wing as a flat plate for boundary layer analysis. a) Calculate the Reynolds number for the wing. b) Calculate the boundary layer thickness at the trailing edge of the wing assuming fully laminar flow. c) Calculate the boundary layer thickness at the trailing edge of the wing assuming fully turbulent flow. d) Calculate the skin friction drag on the full wing assuming laminar flow transitions to turbulent flow at a critical Reynolds number 5.8 x 105.

Problem 2 A Beechcraft Bonanza wing has the following dimensions: - chord = 1.4 m; - span (wing tip to wing tip) = 7m and - wing is roughly rectangular in shape. This plane is flying at 30 m/sec under standard sea level conditions. Model this wing as a flat plate for boundary layer analysis. a) Calculate the Reynolds number for the wing. b) Calculate the boundary layer thickness at the trailing edge of the wing assuming fully laminar flow. c) Calculate the boundary layer thickness at the trailing edge of the wing assuming fully turbulent flow. d) Calculate the skin friction drag on the full wing assuming laminar flow transitions to turbulent flow at a critical Reynolds number 5.8 x 105.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.26P

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