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Post by Br. Marius on Feb 8, 2015 16:55:48 GMT
A main rotor and helicopter characteristics are given as:
Rotor 4 blades, radius = 25 feet, chord = 1.5 feet Tip speed = 700 feet/sec, flap frequency = 1.036/rev Lock number = 8.0 Airfoil CL = 5.73α, Cd = 0.01 Vehicle Weight = 18,000 lbs h = 6.0 ft, lT = 32 ft flat plate area = 25 ft2 xcg = 2 feet forward of shaft axis, ycg = 0 Engine shaft HP = 2000 Assume MxF = 0, and MyF = 0 Assume uniform induced inflow in hover and forward flight with correction factors κhover = 1.15, and κFF = 1.00
(c) Plot control settings (θ0, θ1c, θ1s), flap response (β0, β1c, β1s) and vehicle orientation (αs, φs) with forward speed (0-150 knots) for xcg = 2 ft , ycg = 0 and discuss results
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Post by Br. Marius on Feb 10, 2015 16:57:48 GMT
The plots are at the end of the code...though I'm not sure why my lateral cyclic flapping is going up with speed. Attachments:HW2 Code and Output.pdf (171.67 KB)
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Deleted
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Post by Deleted on Feb 11, 2015 14:01:29 GMT
Br. Marius For your mu values did you convert those knots into feet per second? Just a minor adjustment
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Post by Br. Marius on Feb 11, 2015 14:51:00 GMT
Oh yeah--good call. Thanks!
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Post by Deleted on Feb 11, 2015 19:41:49 GMT
Br. Marius also your lambda hover is not calculated correctly it seems you have test(1) = sqrt(0.5*kh*CT); where kh should be outside the sqrt. We are not getting the same answer for hover SHP and climb rate in hover. I am getting 1933 HP
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