Fox and McDonald's Introduction to Fluid Mechanics
9th Edition
ISBN: 9781118912652
Author: Philip J. Pritchard, John W. Mitchell
Publisher: WILEY
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Textbook Question
Chapter 9, Problem 131P
Assume the Boeing 727 aircraft has wings with NACA 23012 section, planform area of 1600 ft2, double-slotted flaps, and effective aspect ratio of 6.5. If the aircraft flies at 150 knots in standard air at 175,000 lbf gross weight, estimate the thrust required to maintain level flight.
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Chapter 9 Solutions
Fox and McDonald's Introduction to Fluid Mechanics
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- Assume the stabilizer of an airplane is a flat plate. If the transition /critical RN 750,000, what is the skin-friction drag of a rectangular stabilizer having a span of 1.73 m and a chord of 0.81 m at a speed of 44.7 meters per second? Assume standard sea level conditions.-round off to 4 decimal places-show complete solutionarrow_forwardThe measured lift slope for the NACA 23012 airfoil is 0.1080 degree−1,and αL=0 = −1.3◦. Consider a finite wing using this airfoil, with AR = 8and taper ratio = 0.8. Assume that δ = τ . Calculate the lift and induceddrag coefficients for this wing at a geometric angle of attack = 7◦.arrow_forwardThe lift curve for the 4 digit NACA 2421 airfoil is shown in the Figure. Consider a wing with AR = 8, sweep ? = 15 ???, and airplane flies at the Mach number equal to 0.3. The Oswald efficiency span number ?1 = 0.95 Calculate the lift slope for the finite wing. Clearly show the formula and explanations in the solution.arrow_forward
- Consider Mach 4 flow at standard sea level conditions over a flat plateof chord 5 in. Assuming all turbulent flow and adiabatic wall conditions,calculate the skin-friction drag on the plate per unit span.arrow_forwardConsider an NACA 2412 airfoil with a 2-m chord in an airstream with avelocity of 50 m/s at standard sea level conditions. If the lift per unit spanis 1353 N/m, what is the angle of attack?arrow_forwarda)What is the impact of increasing Reynolds number on skin friction and pressure drags over an airfoil? What can be happened for separation in this case? b) What is an adverse pressure gradient and where does it occur on an airfoil (show that on a sketch)? c) Why lift-to-drag ratio is an important parameter for an aircraft? d)How can changing in altitude affect the aircraft power required, PR? Show thatmathematically and graphically?arrow_forward
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