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Local flow in the vicinity of an aircraft in gliding flight

机译：滑行飞行中飞机附近的局部流量

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摘要

For the determination of the flight speed V_∞ of an aircraft from inflight measurements of a local velocity V, a detailed knowledge of the relation between local flow quantities V,α,β,p,ρ, T in the flow field of the aircraft and the corresponding free stream quantities V_ ∞,α_∞,β_∞,p_∞,ρ_∞,T_∞ is necessary. For this purpose a higher order panel method has been applied to calculate this relation for the aircraft Dornier Do 128-6. In a first step the clean configuration without propellers has been considered and in order to validate the calculations gliding flights have been carried out. For the position at the tip of the noseboom of the aircraft considerable deviations between the free stream and the local flow quantities have been found. In a typical low speed flight condition the local angle of attack is 0.56°larger and the velocity is 2.5/100 lower than the free stream quantities. The agreement between theory and flight tests is good, but further improvements are necessary.
机译：为了从飞行中对局部速度V的飞行测量中确定飞机的飞行速度V_∞，需要详细了解飞机流场中局部流量V，α，β，p，ρ，T与相应的自由流量V_∞，α_∞，β_∞，p_∞，ρ_∞，T_∞是必要的。为了这个目的，已经对飞机Dornier Do 128-6应用了一种更高阶的面板方法来计算这种关系。第一步，考虑了没有螺旋桨的清洁配置，为了验证计算结果，进行了滑行飞行。对于飞机鼻梁尖端的位置，已经发现自由流与局部流量之间存在相当大的偏差。在典型的低速飞行条件下，局部迎角要比自由流量大0.56°，速度要低2.5 / 100。理论和飞行测试之间的一致性很好，但是还需要进一步改进。

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