襟翼气动载荷测量方法优化

襟翼是飞机的重要增升翼面。 为获取准确的襟翼气动载荷,需要在襟翼上布置测压孔并进行风洞试验。 基于 CFD 仿真结果分析了某型襟翼压力分布规律,并基于此优化该型飞机襟翼的低速风洞试验测压孔布置方案,研究了不同插值方法对垂向力和铰链轴力矩测量结果准确性的影响。 结果表明,靠近前缘处压力非线性较强,弦向比例 0. 15 ~ 0. 3,0. 3 ~ 0. 5,0. 5 ~ 0. 8,0. 8 ~ 1 接近分段线性分布;对该型襟翼可取弦向比例为 0. 04,0. 07,0. 15,0. 3,0. 5,0. 8 来布置测压孔;对压力分布进行分段线性插值得到的垂向力及铰链轴力矩测量误差不高于- 13% ;用三次样条插值方法的误差不超过- 6% ,明显小于前者。 提出的测压孔布置方案可显著提高襟翼低速风洞试验气动载荷测量准确性,在襟翼风洞测压试验设计及气动载荷测量领域具有一定的参考意义。

Optimization of flap aerodynamic load measurement method

Flap is an important lifting surface of aircraft. In order to obtain accurate flap aerodynamic load, it is necessary to arrange pressure taps on the flaps and carry out wind tunnel tests. Based on the CFD simulation results, the pressure distribution law of a certain type of flap was analyzed, and based on this, the layout scheme of pressure taps scheme for the low-speed wind tunnel test of this type of aircraft flap was optimized. The influence of different interpolation methods on the accuracy of measurement results of vertical force and hinge axis torque was studied. The results show that the pressure nonlinearity near the leading edge is strong; the pressure with chord ratio of 0. 15 ~ 0. 3, 0. 3 ~ 0. 5, 0. 5 ~ 0. 8 and 0. 8 ~ 1 is close to piecewise linear distribution. For this flap, the pressure taps shall be arranged at the chord ratio of 0. 04, 0. 07, 0. 15, 0. 3, 0. 5 and 0. 8. The measurement error of vertical force and hinge axis torque obtained by piecewise linear interpolation of pressure distribution is no more than -13% . The error of cubic spline interpolation method is less than -6% , which is significantly smaller. The proposed layout scheme of pressure taps can significantly improve the accuracy of aerodynamic load measurement in flap low-speed wind tunnel test, and has certain reference significance in the field of flap wind tunnel pressure test design and aerodynamic load measurement.