Modifications of the equations for distribution of circulation for tapered, sweptback wings with streamwise tips in the supersonic flow presented in NACA TN 2643 paper
Dejan Ninkoviæ, MSc (Eng)[1])
In NACA TN 2643 paper [1] equations for distribution of circulation resulting from a constant angle of attack, constant rate of roll and constant rate of pitch, for series of thin, tapered, sweptback, isolated wings with streamwise tips in supersonic flow, are presented. Based on this equations for determination of static and dynamic derivatives values, software G.R.O.M. [2], [3], was developed. In the process of checking, within the presented equations for distribution of circulation, mistakes causing the discontinuities in certain zones of the wings arose, thus violating the basic request that those functions must be continuous. This caused the necessity for equation modifications in order to neutralize discontinuities. Modified equations are presented in the form of tables, mark of the zone in which the modification has been made included, as well as distribution of circulation in the form of diagrams [2], [3].
Key words: winds dynamics, supersonic flow, aerodynamic derivatives, velocity potential, software.