Engineering, 02.03.2020 21:00, parosil

Consider the data for the NACA 0012 airfoil at an angle of attack of 8 degrees. First find the low speed section lift coefficient (Appendix B), and estimate the critical Mach number using the NACA Handbook (page number 115 of the handbook, page 117 of the pdf).

G Problem 6. Using the information from Problem 5, determine what the value of the low speed coefficient of pressure is for the NACA 0012 for an 8 degree angle of attack. Do your results correspond to the notion of thick, medium and thin airfoils? Explain this result.

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Consider the data for the NACA 0012 airfoil at an angle of attack of 8 degrees. First find the low s...