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Investigation of the Model Wake Blockage Effects at High Angles of Attack in a Low-Speed Wind Tunnel
|關鍵字:||low speed wind tunnel|
high angle of attack
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本文以試驗探討風洞模型尾流阻塞之影響，對於高攻角姿態下的試驗模型所測試之數據，需執行修正以獲得正確之氣動力係數。本文利用2.2 × 3.1公尺低速風洞之模型阻力及風洞壁壓力數據分析探討尾流阻塞效應，測試過程以不同大小的圓形平板來模擬試驗模型之高攻角狀態。數據分析結果將以一簡單的方程式來修正模型尾流的阻塞效應，為了驗證此一修正方程式，則以NASA TP-1803模型執行測力試驗，結果驗證修正後之數據二者相吻合。
Excellent maneuverability at high angle of attack flight is important objectives in the future fighter design. When a jet fighter operates at high angles of attack the resulting aerodynamics can be highly nonlinear because of the complicated flow field around the configuration, including unsteady boundary layer, vortex generating, translating, developing / bursting, post stall departures, spin and so on, in addition to their mutual interaction. To improve the fidelity of measured aerodynamic characteristics at high angle of attack for modern jet fighters, the model wake blockage effect is examined in this paper. The wake blockage effect in the 2.23.1 meters low speed wind tunnel is investigated experimentally by analyzing the drag and wall pressure measurements. Circular flat plates in different sizes are used to simulate a test model at high angles of attack. The present analysis results in simple formulas for the corrections of model wake blockage effect. To verify the present correction formula, the NASA TP-1803 model is force-tested in the tunnel. The present corrected test data agree very well with the NASA TP data. It is suggested to use NASA TP-1803 as the standard model to confirm the correction of test data in the tunnel annual instrumental calibration and maintenance.
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