CAJ | 학술논문

运用数值模拟手段分析了一种双圆弧超临界环量控制翼型,它具有高速巡航短距起降双重优势,初步探讨了这种超环量翼型在起飞不同阶段和不同飞行迎角下升阻力性能变化规律。在此基础上对这种翼型进行了几何优化,结果表明,射流缝高度约为环量翼型弦长的0.2%;环量襟翼偏转角度为30°;铰链旋转点在弦长88.06%～89.85%之间时,升阻力性能最优。
운용수치모의수단분석료일충쌍원호초림계배량공제익형,타구유고속순항단거기강쌍중우세,초보탐토료저충초배량익형재기비불동계단화불동비행영각하승조력성능변화규률。재차기출상대저충익형진행료궤하우화,결과표명,사류봉고도약위배량익형현장적0.2%;배량금익편전각도위30°;교련선전점재현장88.06%～89.85%지간시,승조력성능최우。
This paper analyzes a supercritical circulation control airfoil of dual-radius used by numerical simulation,which has the dual advantages of cruise efficient short take-off and landing（STOL）.The relation between lift and drag performance and the different stages and different angles of attack is discussed.Then this airfoil geometry will be optimized,the numerical results indicate that the jet gap height is about 0.2% of the airfoil chord,the deflection angle of airfoil flap is 30 degree,the rotating hinge point at 88.06%～89.85% of airfoil chord and when the optimal lift and drag performance are obtained.