Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 4, Problem 4.7P
For the airfoil given in Problem 4.6, calculate
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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...
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- = 3570 T AC =144 Example: 1.5 ft It is desired to determine the drag force at a given speed on a prototype sailboat hull. A model is placed in a test channel and three cables are used to align its bow on the channel centerline. For a given speed, the tension is 40 lb in cable AB and 60 lb in cable AE. Flow 4 ft Determine the drag force exerted on the hull and the tension in cable AC. Choc ug the h- as the free hod- DApress thearrow_forwardQuestion 2: Consider the 5000kg aircraft below being in a 1000m radius looping maneuver (Fig.2). There are 4 forces acting on the aircraft (Weight, Thrust, Lift, Drag). Assuming that they are all approximately perpendicular to eachother at points A,B,C, calculate the following: A. Calculate the Lift Forces at points A, B, C if the aircraft was at a constant speed of 350km/h throughout the maneuver. B. Calculate the Lift Forces at points A, B, C if the aircraft starts the maneuver at point A at a speed of 400km/h, but reduces its speed with constant acceleration so that the pilot feels weightless at point C. C. A human can withstand earth's gravity was more than 9 times what it is now, we would not survive. What is the maximum of 9 times the gravitational acceleration, i.e. if the maximum speed the pilot can enter this maneuver? Figure 2: Looping Aircraftarrow_forwardGiven A Lexus IS 350, 2010 car model specifications Engine power Pin = 234kw Top speed VT=230km Mass of the car = 1600kg Drag coefficient Cd = 0.274 Cross-sectional area A = 2.57m² Calculate the following a) Assume the car is moving at its top speed, if we think about forces, the force F which is pushin the car forward must win the restricting forces. The main restricting forces are air resistance and rolling resistance of tires Fr, these forces can be calculated using the following equations. 1 F₂ pCaAv² F₁ = μ₂N In these equations, p is the density of air, ur is the coefficient of rolling friction and N is the support force of the road. Let's now assume that μ, 0.01 and p = 1.25 kg/m³; these are quite good approximations. Calculate the force F needed to keep the car moving at its top speed VT (Hint: at top speed, a = 0.) b) The force F we just calculated is the output force that we get out of the drivetrain, while the engine power specified by manufacturer is the input power that the…arrow_forward
- If 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_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_forwardB2 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_forward
- Compute for the lift force acting on a wing with an area of 56 sq. ft., velocity of 75 ft/s at an altitude of 5000 ft. Cl of the wing is 0.75. Calculate the drag of a certain wing with an area of 20 sq. meters , velocity of 75 m/s at an altitude of 2000m . Cd of the wing is 0.05. Compute 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_forwardProblem 4 – Consider the isentropic flow over an airfoil. The freestream conditions correspond to a standard altitude of 10,000 ft and M, = 0.82. At a given point on the airfoil, M = 1.0. Calculate P and T at this point.arrow_forwardIn the following figure, the length ration between aerofoil 1 and aerofoil 2 is OA = 3:1. oa acrofoil I acrofoil 2 What is the ratio between ZBOC and Zboc? ZBOC Zboc Checkarrow_forward
- AAAAAAAAAAAAAAAAAAAAAAAAAAAAAAA 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_forwardAerodynamic Model: - Circular Disk Inside Dia.= 40 mm Outside Dia.= 80 mm Angle of Attack= 15 Degree Lift Force= 0.38 N Drag Force=0.40 N Wind Velocity= 20 m/sec Air Temperature= 30 oC (Note: Take Air Density at 30 oC) Required: - Find Lift and Drag Coefficient at 15 Degree Attack Angle.arrow_forward2. The table below shows experimental data for the shape and pressure distribution on the upper and lower surface of an airfoil at zero angle of attack. X 0 0.25 0.5 0.75 1 Y Fx = Yu 0 0.0952 0.0922 0.0588 0 (Pu dYu dx - Calculate the drag and lift force on the airfoil by numerically evaluating the integrals Fy (P₁-P₂)dx = √ ( P₁ - 1 Pi Y₁ 0 -0.0254 -0.0144 -0.0052 0 dv) Y = Yu (x) dx y = Ye (x) Pu 1.000 -1.640 -0.786 -0.212 0 x Pi 1.000 0.589 0.426 0.322 0 Use finite difference approximations of the derivatives and the composite Simpson's rule to evaluate the integrals. Hint: Use central differences to estimate the derivatives wherever possible since they are more accurate than forward or backward differences.arrow_forward
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