Reference 12 contains inviscid theory calculations for theupper and lower surface velocity distributions V(x) over anairfoil, where x is the chordwise coordinate. A typical re-sult for small angle of attack is as follows:xlcVIU„(upper)VIU„(lower)0.00.00.00.0250.970.820.051.230.980.11.281.051.130.21.290.31.291.160.41.241.160.61.141.080.80.990.951.00.820.82Use these data, plus Bernoulli's equation, to estimate(a) the lift coefficient and (b) the angle of attack if theairfoil is symmetric.

For the same datum, the relation between the velocity and pressure between two points can be…

Answered: Reference 12 contains inviscid theory…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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The so-called Rocket Man, Yves Rossy, fl ew across the Alps in2008, wearing a rocket-propelled wing-suit with the followingdata: thrust = 200 lbf, altitude = 8,200 ft, and wingspan = 8 ft(http://en.wikipedia.org/wiki/Yves_Rossy). Further assume awing area of 12 ft2, total weight of 280 lbf, CDq = 0.08 for thewing, and a drag area of 1.7 ft2 for Rocket Man. Estimate themaximum velocity possible for this condition, in mi/h.
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Outside an inner, intense-activity circle of radius R , a tropicalstorm can be simulated by a polar-coordinate velocitypotential ϕ ( r , θ ) = U o R θ , where U o is the wind velocity atradius R . ( a ) Determine the velocity components outsider = R . ( b ) If, at R = 25 mi, the velocity is 100 mi/h and thepressure 99 kPa, calculate the velocity and pressure atr =100 mi.
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Local boundary layer effects, such as shear stress and heattransfer, are best correlated with local variables, rather usingdistance x from the leading edge. The momentum thicknessθ is often used as a length scale. Use the analysis of turbulentflat-plate flow to write local wall shear stress τw in terms ofdimensionless θ and compare with the formula recommendedby Schlichting: Cf ≈ 0.033 Reθ -0.268.
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Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m.Calculate the boundary layer thickness at the trailing edge of plate and drag force on one sideof plate if:a. Surface of plate is smooth.b. Surface of plate is rough.The air properties at 20 °C are: Density, ? = 1.2 kg/m3and dynamic viscosity, ? = 1.8x 10-5kg/m·s and kinematic viscosity, ν = 1.516×10-5m2/s. kindly give me the solution of this problem with correct and logical reasoning.

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