Question: question 2.b solving using matlab 2. Cambered Airfoil (NACA2412) Fig. 2 NACA 2412 (a) Explain what each digit of NACA 2412' stands for. (5pts) b)

 question 2.b solving using matlab 2. Cambered Airfoil (NACA2412) Fig. 2 question 2.b solving using matlab

2. Cambered Airfoil (NACA2412) Fig. 2 NACA 2412 (a) Explain what each digit of NACA 2412' stands for. (5pts) b) Obtain the Co distribution along the surface (Qe vs. x/c) from -5o to 20 angle of attack at intervals of 5 with constant-strength vortex panel method. (10pts) (c) Plot the C versus AOA and obtain the zero-lift-angle. (15pts) (d) Compare the result of (c) with that from experiments, and discuss the limitation of the panel methods. (10pts) (NOTE) 1. Experimental results are also given at homepage c aio ive homepage

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