Loose Leaf for Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259683992
Author: Anderson, John
Publisher: McGraw-Hill Education
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Chapter 4, Problem 4.2P
Consider an NACA 2412 airfoil with a 2-m chord in an airstream with a velocity of 50 rn/s at standard sea level conditions. If the lift per unit span is 1353 N/m, what is the angle of attack?
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Consider 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?
Compute 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 - 3.5
Consider an infinite wing with an NACA
1412 airfoil section and a chord length of
1 m. The wing is at an angle of attack 5°
in an airflow velocity of 44 m/s at
standard sea-level conditions. Calculate
the lift, drag, and moment about the
quarter chord per unit span.
Chapter 4 Solutions
Loose Leaf for 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...
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- 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_forwardAn airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The airfoil has an aspect ratio of 10 with a span of 36 m. Using the airfoil data as in Fig. 3, determine the lift and drag forces. Then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2. wWw wwarrow_forwardFor the shown continuously circular (i.e. not parabolic) arc airfoil with sharp corners of each 8 = 5°, at 0° angle of attack with Mo = 3 and assuming steady, two-dimensional flow, calculate the: a) pressure coefficient distribution; b) lift coefficient; c) drag coefficient. Moo 8 ********* 8arrow_forward
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- Consider 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 strength of the steady-state starting vortex.arrow_forwardThe two spheres stand with a stop element as in the figure. The spheres are connected with negligible weight rod. What is the minimum air velocity U (m/s] for rotating of the spheres? (Note: Take par=1.225 kg/m, Prater-998 kg/m and u=1.78*10 kg/ms. Spheres are made of steel material with SG=5,41. Take drag coefficient of spheres is 0,41). D=2 cm 10 cm Hinge Stop 45 10cm D-Icmarrow_forwardA light combat aircraft weighs 75,000 N and has a wing area of 27 m?. The maximum lift coefficient with high-lift devices is 1.8, and the structural limit load factor is 6.0. While flying at 250 km/h, the aircraft makes a 90 deg turn in 8 s at sea level holding a constant altitude and at an angle of attack such that the lift-to-drag ratio is 8.0. Find (a) the bank angle, (b) load factor, (c) radius of turn, and (d) the thrust required. [Answer: (a) µ = 54.26 deg, (b) n = 1.7120, (c) R %3D 353.7665 m, and (d) T = 16,050 N.)arrow_forward
- An airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The airfoil has an aspect ratio of 10 with a span of 36 m. Using the airfoil data as in Fig. 3, determine the lift and drag forces. Then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2. 2.0 0.024 1.6 0.020 1.2 0.016 0.8 S 0.012 0.4 0.008 0.004 -0.4 -0.8 -0.4 0.4 0.8 1.2 -8 8 16 24 CL a (degrees) 0.2 -0.2 1.0 xlc Figure 3: NACA 23012 airfoil characteristics of task 3.arrow_forwardmust use thin airfoil theory Need only handwritten solution only (not typed one).arrow_forward5) A wedge airfoil is placed in a supersonic flow at M = 2. G. Calculate the lift and drag coefficients at 4° angle of attack. Hint: Consider the free-stream pressure at the base of the airfoil. 4° Pooarrow_forward
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