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G.R.O.M. software for determining the values of aerodynamic derivatives for isolated wing in
supersonic flow Dejan Ninkovic
Software G.R.O.M., presented in this paper, is developed in order to calculate the values of aerodynamic derivatives – 1 the lift force with respect to the angle of attack; 2 drag force with respect to the angle of attack on the square, as static derivatives; 3 roll-dumping moment with respect to the rate of roll; 4 pitch-dumping moment with respect to the rate of pitch, as dynamic derivatives. Linearized theory of supersonic flow is applied for the wing of vanishingly small thickness with the end parallel to free stream, with the condition that leading and trailing edges must be supersonic with respect to free-stream velocity component normal to the edge. It is assumed that the leading edge is sweptback, while two types of the trailing edge were tested (sweptback and unswept). The results of calculation of aerodynamic derivatives, obtained by G.R.O.M. program, were compared to the corresponding results calculated by Missile Datcom 97 program. High accordance of these two sets of data could be assumed as validation of G.R.O.M. software, signifying its usefulness for engineering practice in the supersonic wing aerodynamic loading calculations.
Key words: aerodynamic derivates, supersonic flow, wing, aerodynamic load, lift force, drag force, roll-dumping moment, pitch-dumping moment, software.
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