# aerodynamics homework

Feb 3rd, 2012
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Exercise 3: Lift and Airfoils Purpose Evaluate the relationships between Coefficient of Lift (CL) and Angle of Attack (AOA), Airfoil Camber, and Airfoil Thickness and the variables of the Lift Equation using graphs and equations. If you are able, review the concepts using an on-line simplified simulated Wind tunnel. Scope (Questions 1-4) Looking at Dole and Lewis textbook Figure 4.

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Exercise 3: Lift and AirfoilsPurposeEvaluate the relationships between Coefficient of Lift (CL) and Angle of Attack (AOA), Airfoil Camber, and Airfoil Thickness and the variables of the Lift Equation using graphs and equations. If you are able, review the concepts using an on-line simplified simulated Wind tunnel. Scope(Questions 1-4) Looking at Dole and Lewis textbook Figure 4.4 and Figure 4,3, you will evaluate Lift Curve slope Parameters of a Symmetrical (NACA 0012) and Cambered Airfoil (NACA 4412) of similar thickness and evaluate the thickness effect on Coefficient of Lift and AOA for cambered airfoils of different thicknesses (NACA 4412 and NACA 4406)1. Find the CLmax for the two airfoils in Figure 4.4.What is the relationship between Camber and CLmax ? AnswerCLmax = 1.5 (CAMBERED) CLmax = 1.3 (SYMMETRICAL)CLmax is directly proportional to Camber2. Find the AOA at Zero Lift for the two airfoils in Figure 4.4.What is relationship between Camber and zero lift (CL = 0)?.AnswerAOA for Cambered is -3 while for symmetrical is 0 and is inversely proportional to Camber3. Find the AOA at CLmax for the two airfoils in Figure 4.4.What is the relationship between Camber and Stall AOA?.AnswerAOA at CLmax for Cambered is 140 and for symmetrical is 180 and is inversely proportional to Camber4. Looking at Figure 4.3, what is the relationship between airfoil thickness, CLmax and AOA? AnswerGreater the thickness greater the CLmax and AOA(Questions 5-7) With some

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