HW1 Solution Manual

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

Info iconThis preview shows pages 1–6. Sign up to view the full content.

View Full Document Right Arrow Icon
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
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
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
Background image of page 2
First Plot Second Plot:
Background image of page 3

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
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.
Background image of page 4
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
Background image of page 5

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Image of page 6
This is the end of the preview. Sign up to access the rest of the document.

Page1 / 7

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

This preview shows document pages 1 - 6. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online