A study of the effect of the frequency of the lowest wing structural mode on the airplane center-of-gravity dynamic-response factor was made by employing simplified transfer functions. It was found that the simplified transfer function adequately predicted the maximum, value of the incremental normal-load-factor response at the airplane center of gravity to isosceles triangle pulse elevator inputs.nThe results of the study are presented in the form of preliminary design charts which give a comparison between the dynamic-response factors of the semi¬rigid case and the airplane longitudinal short-period case and between the dynamic-response factors of the semirigid case and the steady-state value of the air¬plane longitudinal short-period response.
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