摘要:
基于缩比为1/7的F-14全机模型在马赫数Ma=0.73,0.90,1.05,1.20,1.39,迎角α=-4°~20°,侧滑角β=-8°~8°时的风洞测压试验数据,对钝头机体用嵌入式大气数据传感系统(Flush Air Data Sensing System, FADS)的3个校准参数上洗角、侧洗角及形压系数进行了校准。结果表明,基于三点式算法的不同测压点选择方案对上洗角及侧洗角的影响较大,与驻点测压孔呈对称配置的测压点校准效果较好,且上洗角与侧洗角的校准是相互独立的。而形压系数的校准与马赫数及有效迎角、有效侧滑角相关,随着马赫数的增加,形压系数数值上趋近于0。
Abstract:
Based on the wind tunnel pressure data of a l/7-scale model of the F-14 airplane, three parameters of the FADS (Flush Air Data Sensing System,FADS)system,the angle-of-at-tack flow correction angle,the angle-of-sideslip flow correction angle,and the shape and com-pressibility parameter,were calibrated for applying to the vehicle with blunt fore-bodies.The wind-tunnel test Mach numbers were 0.73,0.90,1.05,1.20,and 1.39.Angles of attack were varied in 2°increments from -4°to 20°.Sideslip angles were varied in 2°increments from -8 ° to 8°.The calibration results show that different pressure points have great influence on the cali-bration of the angle-of-attack flow correction angle and the angle-of-sideslip flow correction angle based on the triple algorithm.And the best calibration results can be determined by the pressure points in a symmetrical configuration about the stagnation pressure point.And the calibration for the angle-of-attack flow correction angle is independent of the calibration for the angle-of-sideslip flow correction angle.As to the shape and compressibility parameter,it is related to the effective angle of attack,the effective angle of sideslip,the Mach number,the vehicle shape and other sys-tem factors.With the Mach number increases,the value of the shape and compressibility param-eter tends to zero .
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