MAE2_Airplane_Build

MAE2_Airplane_Build - Klein Flugtag Design Notes II MAE 2...

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Klein Flugtag Design Notes II MAE 2
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2 MAE 2 Equations of Motion The equations of motion for gliding flight are expressed as: Assume sufficient lift force is available to maintain flight after the airplane leaves the launch tube. dV dt =− V 2 2 B g sin dh dt = V sin V = velocity = flight pathangle = density g = gravity dx dt = V cos d dt = 1 V [ V 2 2 A g cos ] h = altitude x = range t = time B = m S C D A = m S C L A = V b 2 2 g cos b V b = boost velocity b = launchangle B = A C L C D
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3 MAE 2 Airplane Simulations 4 6 8 10 12 14 16 0 5 10 15 20 25 30 Boost Velocity (m/s) Maximum Range (m) L/D = 2 L/D = 6 L/D = 10 L/D = 14
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4 MAE 2 4 6 8 10 12 14 16 0 5 10 15 20 25 30 35 Launch Angle Boost Velocity (m/s) Maximum Range (m) 54 deg Launch Angle 18 deg 36 deg L/D = 6
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5 MAE 2 Wing Design for High Lift A cambered airfoil shape increases the lift coefficient. Examples of flapped airfoils are included in Appendix D. Build a rigid wing with a specified two-dimensional airfoil shape.
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This note was uploaded on 01/05/2011 for the course MAE 2 taught by Professor Nomura,k during the Fall '08 term at UCSD.

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MAE2_Airplane_Build - Klein Flugtag Design Notes II MAE 2...

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