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.

1

explanation:

the equation above shows how temperature f, measured in degrees fahrenheit, relates to a temperature c, measured in degrees celsius. based on the equation, which of the following must be true?

a temperature increase of 1 degree fahrenheit is equivalent to a temperature increase of

5

9

degree celsius.

a temperature increase of 1 degree celsius is equivalent to a temperature increase of 1.8 degrees fahrenheit.

a temperature increase of

5

9

degree fahrenheit is equivalent to a temperature increase of 1 degree celsius.

a) i only

b) ii only

c) iii only

d) i and ii only

answer:

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explanation: