Unformatted text preview: Problem 3: With the tail in place, the appropriate equation to use would be . Use to obtain a w = 0.09 deg1 and = 0.2. (You compute the moment.) The slope of the C mα curve is = 0.039 deg1 . The aircraft is stable. For static balancing, we need to be positive. With . Hence, this a/c is statically unbalanced. See if the tail can be fixed to make this a/c balanced. We need to pick i t so that is positive, resulting in Fot i t close to this value, the trim α will be close to zero – you may not like it....
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 Fall '08
 Yousuff
 Addition, statically unstable aircraft, wing body model, 0.039 deg

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