Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 19, Problem 19.6P
To determine
The profile of total temperature through the boundary layer is a function of the velocity profile via
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Air flows over a flat plate at 38 m/s, 25°C and 1 atm pressure. The kinematic viscosity of air at 25°C is ν = 1.562 × 10−5 m2/s. If the critical Reynolds number is 5 × 105, at what distance from the leading edge of the plate would transition occur? (Round the final answer to three decimal places.)
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A 0.75 m by3m flat plate is towed at 5 m/s on a 2.5-mm-thick layer of SAE-30 oil at 38°C, with absolute viscocity of 100 cP,that separates it from a flat surface. The velocity distribution between the plate and the surface is assumed to be linear. What force is required if the plate and surface are horizontal?
Chapter 19 Solutions
Fundamentals of Aerodynamics
Ch. 19 - The wing on a Piper Cherokee general aviation...Ch. 19 - For the case in Problem 19.1, calculate the...Ch. 19 - For the case in Problem 19.1, calculate the...Ch. 19 - Consider Mach 4 flow at standard sea level...Ch. 19 - Repeat Problem 19.4 for the case of all turbulent...Ch. 19 - Prob. 19.6PCh. 19 - Prob. 19.7P
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- Consider a Lear jet flying at a velocity of 250 m/s at an altitude of 10 km,where the density and temperature are 0.414 kg/m3 and 223 K,respectively. Consider also a one-fifth scale model of the Lear jet beingtested in a wind tunnel in the laboratory. The pressure in the test section ofthe wind tunnel is 1 atm = 1.01 × 105 N/m2. Calculate the necessaryvelocity, temperature, and density of the airflow in the wind-tunnel testsection such that the lift and drag coefficients are the same for thewind-tunnel model and the actual airplane in flight.arrow_forwardQ2: Air at standard conditions of I atm and 27°C flows over a flat plate at 20 m/s. The plate is 60 cm square and is maintained at 97°C. Calculate the heat transfer from the plate. Answers: Q= 681 W,arrow_forwardpleasearrow_forward
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- A one-third scale model of an airplane is to be tested in water. The airplane has a velocity of 900 km/h in air at −50°C. The water temperature in the test section is 10°C. The properties of air at 1 atm and −50°C: ? = 1.582 kg/m3, ? = 1.474 × 10−5 kg/m·s. The properties of water at 1 atm and 10°C: ? = 999.7 kg/m3, ? = 1.307 × 10−3 kg/m·s. In order to achieve similarity between the model and the prototype, the water velocity on the model should be (a) 97 km/h (b) 186 km/h (c) 263 km/h (d ) 379 km/h (e) 450 km/harrow_forwardA 0.5m x 2m flat thin plate is moved at 5m/s on a 2-mm thick layer of SAE 30 oil at 38 degrees Celsius that separates it from a flat surface. The velocity distribution between the plate and the surface is assumed to be linear. What force is required if the plate and surface are horizontal? (μSAE30 = 0.1 N-s/m2)arrow_forwardThe temperature of a flat plate is Tw = 3Te , where Te is the static temperature of the high Reynolds flow outside the boundary layer, parallel to the plate. What is the minimum value of mach number for the aerodynamic heating to become more relevant than the convective cooling for the plate?arrow_forward
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