Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 19, Problem 19.4P
Consider Mach 4 flow at standard sea level conditions over a flat plate of chord 5 in. Assuming all laminar flow and adiabatic wall conditions, calculate the skin-friction drag on the plate per unit span.
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Consider Mach 4 flow at standard sea level conditions over a flat plateof chord 5 in. Assuming all laminar flow and adiabatic wall conditions,calculate the skin-friction drag on the plate per unit span.
7. Using shock-expansion theory, calculate the lift and drag coefficients for a flat plate at a 5° angle
of attack in a Mach 2.4 flow.
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Chapter 19 Solutions
Fundamentals of Aerodynamics
Ch. 19 - The wing on a Piper Cherokee general aviation...Ch. 19 - For the case in Problem 19.1, calculate the...Ch. 19 - For the case in Problem 19.1, calculate the...Ch. 19 - Consider Mach 4 flow at standard sea level...Ch. 19 - Repeat Problem 19.4 for the case of all turbulent...Ch. 19 - Prob. 19.6PCh. 19 - Prob. 19.7P
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- Calculate the lift and drag coefficiens for a flat plate at a 5◦ angle of attack in a Mach 3 flow.arrow_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_forwardConsider a rectangular wing with a NACA 23015 airfoil that has a maximum thickness of 2.7 ftand a wing span of 20ft if the freestream density, temperature and mach number are 1.22x10^-3 slugs/ft^3, 444 R and 0.2 respectively. Calculate the lift if the coefficient of lift is 0.8. English unit not metricarrow_forward
- The original Flettner rotor ship was approximately 100 ftlong, displaced 800 tons, and had a wetted area of 3500 ft2. Assketched in Fig. , it had two rotors 50 ft high and 9 ft indiameter rotating at 750 r/min, which is far outside the range. The measured lift and drag coefficients for eachrotor were about 10 and 4, respectively. If the ship is mooredand subjected to a crosswind of 25 ft/s, as in Fig. whatwill the wind force parallel and normal to the ship centerlinebe? Estimate the power required to drive the rotors.arrow_forwardConsider laminar flow past a sharp flat plate of width b andlength L. What percentage of the friction drag on the plateis carried by the rear half of the plate?arrow_forwardPlease do it in 1hr plz fastarrow_forward
- 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.arrow_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 strength of the steady-state starting vortex.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_forward
- The Boeing 747 has a wingspan of 65 meters and AR of 7.7. (a)Assuming take off weight of 910,000 pounds and a take off velocity 160 knots, calculate the lift coefficient at take off for standard sea-level conditions.(b) Compare the above result with the lift coefficient for cruise at Mach number of 92% of the speed of sound.arrow_forwardThe 2013 Toyota Camry has an empty weight of 3190 lbf,a frontal area of 22.06 ft2, and a drag coefficient of 0.28. Itsrolling resistance is Crr ≈ 0.035. Estimate the maximumvelocity, in mi/h, this car can attain when rolling freely atsea level down a 4° slope.arrow_forwardConsider a 102 mph airflow over a flat plate with a span of 9.7 ft and a planform area of 60 ft2. The boundary layer transitioned from laminar to turbulent. If the total skin friction drag for the laminar section is 0.858 lbs, determine the location of the transition point. Assume SSLC, Provide answer in feet and round off answer to the nearest thousandths.arrow_forward
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