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MAE2_Lecture10

# MAE2_Lecture10 - Stability and Control II Review Pitching...

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Stability and Control II Review Pitching Moment Derivation Longitudinal Static Stability Neutral Point Static Margin Longitudinal Trim MAE 2 F-100 Super Sabre Cockpit (NASA Image)

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2 MAE 2 Pitching Moment at CG For stability analysis, it is desired to combine all forces (wing and tail) at a common reference point. The center-of-gravity is a commonly used reference point for rigid aircraft. The center-of-buoyancy is a commonly used reference point for balloons and dirigibles. L t D t M act c.g. L w D w M acw L cg M cg D cg L cg = L w L t wing horizontal tail D cg = D w D t = sum of wing lift and tail lift = sum of wing drag and tail drag M cg M acw M act some terms are missing. ..
3 MAE 2 Additional Moment Terms Lift and drag forces from wing and tail will produce additional moment contributions about the center-of-gravity. c.g. M acw M cg = M acw c.g. L w L w cos w L w L w sin w L w w Step 1: Wing moment about a.c. contributes the same moment about c.g. Step 2: Convert wing lift force into components parallel and perpendicular to chord line. chord line chord line

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4 MAE 2 CG Moment from Wing Lift M cg = M acw L w h h acw c L w w z c L w L w w Step 3: Add wing lift contributions to c.g. moment
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MAE2_Lecture10 - Stability and Control II Review Pitching...

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