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- W2937540089 abstract "In general, it takes large time and cost to obtain dynamic stability derivatives of flight vehicles experimentally or numerically. In this study, the pitching dynamic derivatives of aircrafts are predicted by using source-doublet panel method and evaluate its practicality. A free-wake panel method is used for unsteady aerodynamic analysis of an aircraft in forced harmonic pitch oscillation. A treatment for wake-body interaction is applied to take into account the effect of wake from a main wing on a fuselage or tail wing. Calculations are carried out for a single rectangular wing, standard dynamic model(SDM), and DLR-F12 geometries. The dynamic derivatives are predicted based on the time history of the normal force and pitching moment. The unsteady panel method is validated by using numerical and experimental data in literatures and the results of Euler computation using commercial CFD code. For both the time history and predicted dynamic derivatives, the results show reasonable agreement with available experimental data and CFD results. The effect of Mach number and reduced frequency is examined for the SDM case. Within the Mach number range studied, the dynamic derivatives increase with Mach number which is consistent with the tendency observed in the previous studies. The dynamic derivatives are found to be relatively insensitive to the reduced frequency. The results show that the method of the present study provides reasonable accuracy and good efficiency for estimating the dynamic derivatives." @default.
- W2937540089 created "2019-04-25" @default.
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- W2937540089 date "2019-03-31" @default.
- W2937540089 modified "2023-09-25" @default.
- W2937540089 title "PREDICTION OF PITCHING DYNAMIC DERIVATIVES OF AIRCRAFT USING A UNSTEADY SOURCE DOUBLET PANEL METHOD" @default.
- W2937540089 doi "https://doi.org/10.6112/kscfe.2019.24.1.113" @default.
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