Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
expand_more
expand_more
format_list_bulleted
Videos
Textbook Question
Chapter 4, Problem 4.11P
Consider again the NACA 2412 airfoil discussed in Problem 4.10. The airfoil is flying at a velocity of 60 m/s at a standard altitude of 3 km (see Appendix D). The chord length of the airfoil is 2 m. Calculate the lift per unit span when the angle of attack is 4°.
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solution
Students have asked these similar questions
Consider the North American P-51D Mustang. Its wingspan is 37 ft; wing area is 233.6 ft2; and gross weight is 10,100 lb. Assume the Oswald efficiency factor as 0.8. The airplane is flying in steady; level flight at a velocity of 750 mi/h at a standard altitude of 5000 ft.
Calculate the drag due to lift using the concept of span loading.
Consider the following NACA airfoils:
2412, 23012, 23021
a. For each of these airfoils, find the L/D ratio for angle of attack of 0, 4, 8 and 12
b. For each airfoil find the angle of maximum L/D and find the stall angle
c. Find which airfoil will provide the maximum lift for any given geometry and flow
conditions
Consider an NACA 23012 airfoil. The mean camber line for this airfoil is given by
= 2.6595
0.6075
A +0.1147
for 0<
< 0.2025
= 0.02208 (1–) for 0.2025 << 1.0
Calculate (a) the angle of attack at zero lift, (b) the lift coefficient when a = 4°, (c) the
moment coefficient about the quarter chord, and (d) the location of the center of pressure
in terms of xep/c, when a = 4°. Compare the results with experimental data.
and
Chapter 4 Solutions
Fundamentals of Aerodynamics
Ch. 4 - Consider the data for the NACA 2412 airfoil given...Ch. 4 - Consider an NACA 2412 airfoil with a 2-m chord in...Ch. 4 - Starting with the definition of circulation,...Ch. 4 - Starting with Equation (4.35), derive Equation...Ch. 4 - Consider a thin, symmetric airfoil at 1.5 angle of...Ch. 4 - The NACA 4412 airfoil has a mean camber line given...Ch. 4 - For the airfoil given in Problem 4.6, calculate...Ch. 4 - Compare the results of Problems 4.6 and 4.7 with...Ch. 4 - Starting with Equations (4.35) and (4.43), derive...Ch. 4 - For the NACA 2412 airfoil, the lift coefficient...
Ch. 4 - Consider again the NACA 2412 airfoil discussed in...Ch. 4 - For the airfoil in Problem 4.11, calculate the...Ch. 4 - In Section 3.15 we studied the case of the lifting...Ch. 4 - The question is often asked: Can an airfoil fly...Ch. 4 - The airfoil section of the wing of the British...Ch. 4 - For the conditions given in Problem 4.15, a more...
Additional Engineering Textbook Solutions
Find more solutions based on key concepts
How is the hydrodynamic entry length defined for flow in a pipe? Is the entry length longer in laminar or turbu...
Fluid Mechanics Fundamentals And Applications
The solid steel shaft AC has a diameter of 25 mm and is supported by smooth bearings at D and E. It is coupled ...
Mechanics of Materials
A biological fluid moves at a flow rate of m=0.02kg/s through a coiled, thin-walled, 5-mm-diameter tube submerg...
Fundamentals of Heat and Mass Transfer
The moment of inertia Iy for the slender rod in terms of the rod’s total mass m .
Engineering Mechanics: Statics & Dynamics (14th Edition)
List several uses of the arbor press.
Machine Tool Practices (10th Edition)
A pipe flowing light oil has a manometer attached, as shown in Fig, P1.52. What is the absolute pressure in pip...
Fundamentals Of Thermodynamics
Knowledge Booster
Learn more about
Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.Similar questions
- Consider an airfoil at 12◦ angle of attack. The normal and axial forcecoefficients are 1.2 and 0.03, respectively. Calculate the lift and dragcoefficients.arrow_forwardCalculate the lift and moment coefficients using thin airfoil theory approximations for a range of angle of attacks for the following airfoils below. 1. NACA 0008 2. NACA 0018 3. AG04 4. Clark-Y 5. NACA 2415 Angle of attacks taken to be between 0 degree to 15 degree. Also calculate value of Cm at quarter chord. (Cm at 0.25c) for each. Reynolds number 1000000arrow_forwardConsider an NACA 2412 airfoil with a chord of 0.64 m in an airstream at standard sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1254 N/m. Calculate the moment per unit span about the aerodynamic center.arrow_forward
- A NACA 2412 airfoil with a chord of 0.64m is flying in an airstream of standard sea level conditions. The freestream velocity is 70 m/s. Given the lift per unit span is 1,254 N/m. By using the experimental data for NACA 2412 data plot in Figure Q1c, investigatethe angle of attack of the airfoil and the analyze the value of drag per unit spanof the airfoil. Given that at standard sea level, ?=1.789×10-5 kg/m.s.arrow_forwardCompute the lift and drag coefficients for a symmetric, diamond-shaped airfoil with a thickness-to-chord ratio t/c equal to 0.10, flying at Mach 3.5 in air (y=1.4) at zero angle of attack. M₂ - 3.5arrow_forwardAn airfoil has a lift curve slope at 7/rad and angle at zero lift of -3deg. At what angle of attack will the airfoil develop a lift of 120 lbs/ft at 110 mph under SSLC? Assume c = 10ft.arrow_forward
- 3. The airfoil has an angle of attack of 4 deg. What is the lift curve slope if the angle of attack measured from zero lift is -2 deg., lift/span is 1000 N/m with a speed of 200 m/s at 12,000 m. Assume c= 3 m.arrow_forwardIf the pressure difference in the wind tunnel experiment is 50 mmH,0, the density of air is 1.2 kg/m in wind tunnel experiment, and the airfoil span is 204 mm, and the cord length is 98 mm, what is the lift coefficient if the lift force is L=13.4 Narrow_forwardProblem 06.025 - Calculate maximum velocity The Predator UAV has the following characteristics: wingspan = 14.85 m, wing area = 11.45 m², maximum weight = 1110 kgf, and fuel weight = 295 kgf. The power plant is a Rotax four- cylinder, four-stroke engine of 100 horsepower driving a two- blade, variable-pitch pusher propeller. Assume: the Oswald efficiency factor is 0.7; the zero-lift drag coefficient is 0.03; the propeller efficiency is 0.9; and the specific fuel consumption is 0.2 kgf of fuel per horsepower per hour. Calculate the maximum velocity of the Predator at sea level. The maximum velocity of the Predator UAV at sea level is m/s.arrow_forward
- The lift curve for the 4 digit NACA 2421 airfoil is shown in the Figure. -Consider a wing with AR = 12, no sweep, and airplane flies at the Mach number equal to 0.65. 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_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_forwardConsider a standard NACA Five digit aerofoil with h = 0.29 and k_1 = 6.643; x_h = 0.2 Find the zero lift Angle of Anglearrow_forward
arrow_back_ios
SEE MORE QUESTIONS
arrow_forward_ios
Recommended textbooks for you
Principles of Heat Transfer (Activate Learning wi...Mechanical EngineeringISBN:9781305387102Author:Kreith, Frank; Manglik, Raj M.Publisher:Cengage Learning
Principles of Heat Transfer (Activate Learning wi...
Mechanical Engineering
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Cengage Learning
Ficks First and Second Law for diffusion (mass transport); Author: Taylor Sparks;https://www.youtube.com/watch?v=c3KMpkmZWyo;License: Standard Youtube License