Question 2 (10 marks) (2022 Paper) Question 2a The Aerodynamic characteristic of a NACA0015 airfoil is simulated using a Potential Method. The Cp and Tw distributions are presented in Figure Q2(a)-1

and Q2(a)-2 of Appendix 1 respectively. Question 2a(i) Verify boundary layer transition occurrence by identifying the location of the transition Point. Question 2a(ii) Base on the data presented, provide TWO (2) reasons to verify your answer in Q2a(i). Question 2a(iii) Apply the learnt airfoil content, is NACA0015 a symmetrical airfoil? Question 2a(iv) Appraise the Lift-curve Slope (Cle) of this airfoil. Question 2b The airfoil presented in Q2(a) above is used for the design of a wing with Aspect Ratio of 10. Apply the data to calculate the Lift-curve Slope (Cla) of the wing. You may assume the span efficiency factor to be 1.0.