Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 5, Problem 5.4P
The Piper Cherokee (a light, single-engine general aviation aircraft) has a wing area of
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The Piper Cherokee (a light, single-engine general aviation aircraft) has a wing area of 170 ft2 and a wing span of 32 ft. Its maximum gross weight is 2450 lb. The airplane is cruising at 122 mi/h at standard sea level at its maximum gross weight and is in straight-and-level flight. The span efficiency factor e for the complete airplane is generally much less than that for the finite wing alone. Assume e = 0.64. Calculate the induced drag for the airplane. (Round the final answer to two decimal places.)
The induced drag for the airplane is.............lb.
The 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◦.
The test results of a NACA 2518 shows:
Angle of attack
0 deg
8 deg
CL
0.045
0.75
If the airfoil is used to construct a wing with a span of 60 ft and a wing area of 450 square feet.
Determine the wing lift curve slope. (e = 0.88)
Chapter 5 Solutions
Fundamentals of Aerodynamics
Ch. 5 - Consider a vortex filament of strength in the...Ch. 5 - Consider the same vortex filament as in Problem...Ch. 5 - The measured lift slope for the NACA 23012 airfoil...Ch. 5 - The Piper Cherokee (a light, single-engine general...Ch. 5 - Consider the airplane and flight conditions given...Ch. 5 - Consider a finite wing with an aspect ratio of 6....Ch. 5 - Repeat Problem 5.6, except for a lower aspect...Ch. 5 - In Problem 1.19 we noted that the Wright brothers,...Ch. 5 - Consider the Superrnarine Spitfire shown in Figure...Ch. 5 - If the elliptical wing of the Spitfire in Problem...
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- For a new sailboat, a designer wants to determine the drag force that may be expected at a given speed. To do so, she places a model of the proposed hull in a test channel and uses three cables to keep its bow on the center-line of the channel. Dynamometer readings indicate that for a given speed, the tension is 35 lb in cable AB and 40 lb in cable AE. The drag force is exerted in the direction of Flow at point A. –7 ft - B E1.5 ft 4 ft Flow A 4 ft E What is the magnitude of the drag force in Ib? What is the magnitude of the tension force in cable AC in Ib? What is the angle a in degrees measured CCW from the vertical? What is the angle B in degrees measured CW from the vertical?arrow_forwardThe aircraft is flying at a velocity of 50 m/s, at an altitude of 4500 m. Determine the lift/span created by the rectangular wing, with chord of 3 m, and a span of 13 m. The airfoil is flying at an angle of attack of 4 deg, and has the following details. AOA CL -0.5 deg 0 4 deg (unknown) 8 deg 0.7arrow_forwardWhen testing a new car, the car drives with a constant speed v = 140 km/h. Thepower of car’s engine is P = 120 kW and we know that 80% of this power is con-verted to movement. Determine the drag coefficient in air if the cross section of thecar has circular shape, its value is S = 3 m2, and air can be described as a liquidwith viscosity η = 2,2 · 10−3 Ns/m2 and density ρ = 1,2 kg/m3. Calculate theReynolds number and determine if the linear or quadratic drag equation is valid inthis case or neither of them.arrow_forward
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- An aircraft is equipped with a wing of symmetrical airfoils. The lift curve slope of the total aircraft is estimated to be 0CL/Oa = 5.0265 1/rad. The stall angle of attack (AOA) is 12°. Wing area is 16 m2. Use g = g0 and r = rO. What is the aircraft's mass during a flight on which a stall speed of 50 kt was observed?arrow_forwardHandwriting not allow pleasearrow_forwardConsider the NACA 2412 airfoil discussed . The airfoil is flying at a velocity of 60 m/s at a standard altitude of 3 km . The chord length of the airfoil is 2 m. Calculate the lift per unit span when the angle of attack is 4◦.arrow_forward
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