HW1 Solution Manual

HW1 Solution Manual - Homework 1 Solution Manual Problem...

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Homework 1 Solution Manual Problem 1 (1points for each part) Schematic: 1 FBD Part A: Part B: Part C Note: Only the pressure is acting perpendicular to the chord length. Refer to the schematic 1 Note: Only shear stress is acting parallel to the chord length. Refer to the schematic 1 Part D Note: Equation 1.1 and 1.2 from the book. Part E Problem 2 Variable MLT MKS Velocity L/T m/s Density M/L 3 kg/m 3 Pressure M/L*T 2 kg /m*s 2 Pressure/Density L 2 /T 2 m 2 /s 2 Density *Velocity ^2 M/L*T 2 kg/m*s 2 Shear Stress M/L*T 2 kg/m*s 2

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Problem 3(Correct Solution 5 pts; Wrong answer, correct approach 3pts; Wrong approach, some work 1 pt ) Physical Variables: Velocity V, Diameter D, Density ρ, Angular Velocity W, Power P Fundamental Dimensions: Mass, Length, Time Physical Variables (N) = 5 Fundamental Dimensions (K) = 3 Pi Terms = ( N-K) = 2 Repeating Variables: Velocity, Diameter, Density Non Repeating Variables: Power, Angular Velocity 1 st Pi Term: Solve for Kg: 1 +c = 0 c = -1 Solve for s: -3 –a =0 a = -3 Solve for m: 2-3+b+3 =o b =-2 2 nd Pi Term: Solve for Kg: 0 +f= 0 f = 0 Solve for s: -1–d =0 a = -1 Solve for m: -1+e =o e = 1 Problem 4 solutions a) Use the default geometry settings and an angle of attack of 3 degrees, and answer or do the following. Print the plots in the two figures. One point for plots
First Plot Second Plot:

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Is the airfoil symmetric top-to-bottom? Not symmetric ( one point) Label which C p curve is for the upper surface and which is for the lower surface.
Upper curve is for the upper surface and the lower curve is for the lower surface. (1 pt) The value of the boundary layer thickness, theta, given by the program is the nondimensional value (theta = θ /c), where θ is the dimensional boundary layer thickness and c is the chord length. If the airfoil has a chord length c=3m, what is the

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HW1 Solution Manual - Homework 1 Solution Manual Problem...

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