Documented oscillograph recorded multichannel data (primarily F-105D) was used to develop an eight variable mathematical environment model of fighter aircraft response per Mil Spec 8866A mission segments. The F-106 fighter was selected for demonstration of the model. F-106 detailed flight test results, fatigue cyclic test data and 3770 flight hours of normal service response data were available to facilitate evaluation of the model. These data made it possible to empirically compute structural component loads for comparison with F-106 design values. On the basis of these analyses, new design criteria for strength and fatigue are recommended.
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YOST et al. (1972) studied this question.