控制翼缝隙流传热实验研究

EXPERIMENTAL INVESTIGATION OF AERODYNAMIC HEATING BY FLOW THROUGH CONTROL SURFACE GAPS

在Μ_∞=6.5—10,Re_∞=(0.35—3.5)×10~7m^(-1)的来流条件下测量了平板-控制翼上及其展向缝隙内的热流分布,以考察缝隙宽、翼偏转角、缝入口唇缘形状、来流参数对缝内外气动热的影响。

Detailed aerodynamic heating distributions were measured over a flat plate equipped with a flap and inside the gap between the plate and the flap to understand effects of gap width, flap deflection, Reynolds number and Mach number on thermal enviroment in the flap gap. Measurements were made for flap deflection angles of 10°, 20°, 30°, 40°and 90°, with variable leakage by varying gap width at free-stream Mach numbers of 6.5,8 and 10, Reynolds numbers of (0.35—3.5)×10~7 m^(-1) in JF8 shock tunnel and JF4B gun tunnel. The test results indicate that ratio of gap heating rate to local plate value increases with flap deflection, free-stream Reynolds number and decreases with Mach number for turbulent external (separated or attached) flow. With attached flow on the plate ahead of the flap, turbulent heating distributions on both the plate and the flap are not influenced by gap leakage. Within the gap, a separation bubble develops on the upstream face of the gap; heating peak occurs at attached point which is at a distance of 2—3 width of gap from the entrance where low heating rate. is occurs. Gap heating rate is less than local plate value and increases with gap width and bluntness of entrance lip. With turbulent separated external flow, incresing gap width and decreasing flap deflection decrease the size of separation; gap heating rates match or exceed the attached flow plate values and decrease with distance from the entrance, but are not influenced by variation of entrance lip bluntness.