Structural analysis and design of airplanes (1920)
United States. Army. Air Corps · [Washington] · leaf 256
d and rear portion of thefuselage must be figured separately. In computing the rear portion,enough load should be added to the forward panel points to bring thecenter of gravity forward of the rear spar. For the forward portionenough load should be assumed to be subtracted from the tail load… … Fig. 159. Panel Loads in Maximum Air Load Condition C hC^d of tY,n^\ 5to ?
Airplanes
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