空气动力学学报
空氣動力學學報
공기동역학학보
ACTA AERODYNAMICA SINICA
2015年
4期
470-474
,共5页
Re 数效应%转捩%γ-Reθ 模型
Re 數效應%轉捩%γ-Reθ 模型
Re 수효응%전렬%γ-Reθ 모형
Reynolds number effect%transition%γ-Reθ model
基于γ-Reθ转捩预测模型，对使用超临界层流复合翼的飞机进行转捩预测数值模拟。获得机翼在不同 Re数下的自由转捩位置，计算转捩位置与试验数据吻合。结合转捩预测结果和强制转捩试验数据，对全机风洞试验数据进行不同高度的 Re 数效应修正。改变了战斗机只对阻力进行 Re 数效应修正的传统方法，分别对飞机的升力、阻力及纵向力矩进行 Re 数效应修正。
基于γ-Reθ轉捩預測模型，對使用超臨界層流複閤翼的飛機進行轉捩預測數值模擬。穫得機翼在不同 Re數下的自由轉捩位置，計算轉捩位置與試驗數據吻閤。結閤轉捩預測結果和彊製轉捩試驗數據，對全機風洞試驗數據進行不同高度的 Re 數效應脩正。改變瞭戰鬥機隻對阻力進行 Re 數效應脩正的傳統方法，分彆對飛機的升力、阻力及縱嚮力矩進行 Re 數效應脩正。
기우γ-Reθ전렬예측모형，대사용초림계층류복합익적비궤진행전렬예측수치모의。획득궤익재불동 Re수하적자유전렬위치，계산전렬위치여시험수거문합。결합전렬예측결과화강제전렬시험수거，대전궤풍동시험수거진행불동고도적 Re 수효응수정。개변료전두궤지대조력진행 Re 수효응수정적전통방법，분별대비궤적승력、조력급종향력구진행 Re 수효응수정。
Transition significantly affects aerodynamic characteristics of an airplane,such as the drag,lift and pitching moment,and the transition position of supercritical laminar complex wings is greatly influenced by Reynolds number effect.The traditional methods of Reynolds number effect correction are not suitable anymore for those aircraft with supercritical laminar complex wings.Aγ-Reθ model for the transition prediction of an airplane with supercritical lami-nar complex wings is introduced.The transition point could be obtained by this way according to its Reynolds number,and the computational transition points are accord with the wind tunnel tests.The wind tunnel experiment data are corrected and modified by the combination of CFD re-sults and experiment data.The traditional Reynolds number effect correction methods correct the drag only, while this new proposed method corrects the lift,drag and pitching moment respectively and simultaneously.More accurate data for real flight could be obtained from wind tunnel experiment data by this method,and makes the flight safer.
