FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
6th Edition
ISBN: 9781265141387
Author: Anderson
Publisher: MCG
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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 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
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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)
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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?
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What is the angle B in degrees measured CW from the vertical?
Chapter 5 Solutions
FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
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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- The 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_forwardShow that the pressure on the wing surface is increasing with downstream distance. Is this consistent with your calculations showing that the boundary layer is approaching separation? Explain your reasoning.arrow_forward
- The drag coefficient for the car is CD�� = 0.28, and the projected area into the 20∘C∘C airstream is 2.5 m2m2. At this temperature ρa�� = 1.202 kg/m3kg/m3. (Figure 1)Determine the power the engine must supply to maintain a constant speed of V� = 160 km/hkm/h .arrow_forwardAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAA The image below is a cross-section of a Darrieus-type and wind turbine. Find the cross Sectional moment provided by the bottom airfoil under the following circumstances. Calculate the lift coefficient based on the formula CL = 27 (α -αL=c) Assume that stall is not occuring The airfoil has a zero lift angle of attack of O degrees and a sectional drag coefficient of 7x10- -3 10 = 41-7 RPM 6 = 13 degrees R = 188 m V = limls C =017 m Airdensity = 0.91 kg/m3 Find moment in N.m C R co Carrow_forwardAn 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_forward
- A lady on a bicycle is going down a hill. If the initial slope angle θ1 = 5 and she has a constant speed with no braking or pedaling, determine the drag force asserted on bicycle tires by the ground (Assume the total mass for her and the bicycle is 70 kg and neglect air resistance). Question 2 options: F=35.93 N F=0.0483g N F=59.85 N F=0.0523mg N Note:- • Do not provide handwritten solution. Maintain accuracy and quality in your answer. Take care of plagiarism. • Answer completely. • You will get up vote for sure.arrow_forwardQuestion B3 – External Flow The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 15Okm/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5°C and 90 kPa, respectively. a) Calculate the density of the air at cruising altitude. b) Calculate the form drag on the wings. c) Calculate the Reynolds number of the wings.arrow_forwardCompute for the drag of a rectangular wing with a chord of 4.5 ft and a span of 16 ft. if the dynamic pressure 80 psi. Cd of the wing is 0.030.arrow_forward
- B2 is flying at an altitude of 43,000 ft and a speed of 400 KTAS under standard atmospheric conditions. If the average aerodynamic chord is 39,6 ft, calculate the Reynolds number and the average % aerodynamic chord present on the wingarrow_forwardAn airplane has a mass of 68,000kg and has an effective wing area of 122.6m?. Determine the angle of attack (angle between the wing and the horizontal axis) that the wing must make with the oncoming air at a speed of 270km/h so that the lift force (FL) is equal to the weight of the airplane. Assume that the coefficient of lift C varies linearly from 0.70 at 0° to 1.60 at 6°. Take pair = 1.225kgm-3 and g 9.81ms-2. %3Darrow_forward3- Assuming that the velocity distribution in the laminar boundary layer: и = sin 28 Determine the total friction coefficient in terms of the Reynolds number. [1.31/Re, ]arrow_forward
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