Thrust effect on lifting boundary as determined by a WuT

The following part is from an article I recently submitted to be published in the SETP Cockpit magazine and follows up an analysis I had performed few years ago.

To complete this analysis and quantify the effect of the thrust setting on ITR, a specific example is considered. The following figures (3 and 4) are analytically generated and correspond to a high-performance fighter aircraft assuming a 9g limit, a weight of 20,000kg, altitude 20,000 ft and max thrust at that altitude of 20,000lbs. The primary analysis considers a α_max of 50deg and δ=0 (Fig.3(a) and Fig,4(a)), and a sensitivity analysis is performed for α_max of 60 and 40 deg as well (Fig.3(b) and Fig,4(b)).

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