AAE251 HW 5

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Purdue University *

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251

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Mechanical Engineering

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Dec 6, 2023

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1 Name Team Number AAE 251: Introduction to Aerospace Design Homework 5—Wind Tunnels, Lift, and Drag Due Tuesday February 22 nd , 11:59 PM ET on Gradescope Instructions Show all the work and clearly box your final answer. You will not receive full credit for a correct final answer if you don’t show your work. You must use the template provided. Anything that you want the graders to grade must be written legibly within the boxes provided to you. There are multiple steps involved to complete your submission on Gradescope. You can follow the step-by-step guide posted on Brightspace. Select the relevant pages of your final answer for each question in your Gradescope submission.
2 Question 1 (5 points) Consider a low-speed open-circuit subsonic wind tunnel with an inlet-to-throat area ratio of 12. The tunnel is turned on, and the pressure difference between the inlet (the settling chamber) and the test section is read as a height difference of 10cm on a U- tube mercury manometer. The density of air is 1.225kg/m ! and that of liquid mercury is 1.36 × 10 " kg/m ! . Calculate the velocity of the air in the test section. Answer 1:
3 Question 2 (8 points) You are testing a model wing of constant chord length in a low-speed subsonic wind tunnel, spanning the test section. The wing has an NACA 2412 airfoil and a chord length of 0.6 m. The parameters for the full scale and wind tunnel models are as follows: Parameters Full Scale Model Wind Tunnel Model Mach number 0.25 0.25 Density 0.019 kg/m 3 0.034 kg/m 3 Temperature 216.65 K 68.6 K Speed of sound 295 m/s 166 m/s Drag 95.6 N To be computed Assume that we can relate dynamic viscosity to temperature as follows: / #$%& ()%%*+ ,-&*+ / .)++ /01+* ,-&*+ = 1 2 #$%& ()%%*+ ,-&*+ 2 .)++ /01+* ,-&*+ 3 ! " (a) Compute the chord length of the wind tunnel model of the airfoil. (4 points) Answer 2a:
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