Questions 14 Looking at Dole and Lewis textbook Figure 44 an

1. Find the CLmax for the two airfoils in Figure 4.4.What is the relationship between Camber and CLmax ?

2. Find the AOA at Zero Lift for the two airfoils in Figure 4.4.What is relationship between Camber and zero lift (CL = 0)?.

3. Find the AOA at CLmax for the two airfoils in Figure 4.4.What is the relationship between Camber and Stall AOA?.

4. Looking at Figure 4.3, what is the relationship between airfoil thickness, CLmax and AOA?

(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 ? 2. Find the AOA at Zero Lift for the two airfoils in Figure 4.4.What is relationship between Camber and zero lift (CL = 0)?. 3. Find the AOA at CLmax for the two airfoils in Figure 4.4.What is the relationship between Camber and Stall AOA?. 4. Looking at Figure 4.3, what is the relationship between airfoil thickness, CLmax and AOA?

CLmax for NACA4412 is approximately 1.55

CLmax for NACA0012 is approximately 1.35

Relationship between Camber and CLmax is almost circular.

AOA at zero lift for NACA4412 is approximately -2.8

AOA at zero lift for NACA0012 is approximately 0.2

Relationship between Camber and zero lift is linear.

AOA at CLmax for NACA4412 is approximately 15

AOA at CLmax for NACA0012 is approximately 17 (or maybe 18)

(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 Cam

Questions 14 Looking at Dole and Lewis textbook Figure 44 an

Solution

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