| Résumé | Vortex dynamics over more than 50 types of military wing configurations have been experimentally investigated. Diamond and delta wings with sweep back angles from 55° to 75° have been tested. The experiments were conducted in two wind tunnels and a water tunnel with more than 10,000 runs at different test conditions. Investigations include flow visualisations (surface and off-surface flow field and vortex behavior), surface pressures (steady and unsteady pressure), air loads (steady and unsteady loads) and motion histories (harmonic, ramp-and-hold, free-to-roll and “forced” free-to-roll), geometry and Renumber effects in pitch, roll and coning motion plans. The ranges of angle of attack, roll angle and coning angle are 0°~90°, ±180° and ±360° respectively with maximum non-dimensional frequency 0.2 in pitch and roll and 0.6 in coning respectively. The maximum Re number is 3x106 and maximum Mach number is 0.4 in wind tunnel experiments. The comprehensive data sets have been edited into eight volumes of IAR reports while only a brief of the program is presented here. |
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