View the step-by-step solution to:

Question

I am trying to compute aerodynamic coefficients from experimental data.


CL = L [kgf] x 9.81

L [N] -0.240 x 9.81

____________ = ____________ = ______________

q [Pa] x S [m^2] q [Pa] x S [m^2] q [Pa] x S [m^2]



This is co efficient of lift. Data is from a wind tunnel.


Wing/Airfoil characteristics:


b=12 inch/m c= 4 (inch/m) S= 48 (inch^2/m^2) C (with line above)= 4 AR=b^2 / S = 3 TR=1 deg=0


Static air data


P=29.32 (inch HG) Tem (T) = 74.4 [Pa] - is this 31397.331? T (0 degrees C/K) = 27.6 degrees celcius/296.71 k P [kg/m^3]=1.1658 (is this air density?)




So how do I find q? [Pa] - (above?) S (do I take 48 square it and divide by m^2-but what is m?) finally, times by m^2 again...what is m?


Please advise. Thank you

Recently Asked Questions

Why Join Course Hero?

Course Hero has all the homework and study help you need to succeed! We’ve got course-specific notes, study guides, and practice tests along with expert tutors.

-

Educational Resources
  • -

    Study Documents

    Find the best study resources around, tagged to your specific courses. Share your own to gain free Course Hero access.

    Browse Documents
  • -

    Question & Answers

    Get one-on-one homework help from our expert tutors—available online 24/7. Ask your own questions or browse existing Q&A threads. Satisfaction guaranteed!

    Ask a Question
Ask Expert Tutors You can ask 0 bonus questions You can ask 0 questions (0 expire soon) You can ask 0 questions (will expire )
Answers in as fast as 15 minutes