Abstract
Existing methods devised to simplify the tedious classic procedure of performance computation depend either upon generalized parameters or upon approximate curves valid only in a restricted range, with the result tha t calculations usually are not accurate even in the low-speed range and for high speeds are hardly applicable. Inasmuch as the force coefficients (CL and CD) become functions of the speed at high speeds, while the object of the performance computation is to determine the speed through a knowledge of these coefficients, the solution of this interlocking problem becomes extremely cumbersome by the usual analytic means. This paper describes a new method of solution which makes direct use of the actual airplane polars without approximations. The procedure is based on an extension of the Eiffel-Rith coordinate system,'and all scales can be incorporated in a simple transparent chart, thereby eliminating the necessity for specially prepared.graph paper. Compressibility effects are taken into account through the use of constant altitude variable Mach Number polars which are derived from constant Mach Number polars of the true airplane.
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