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在马赫数为6和10的空气流中测量了在球钝头13°/7°同轴双锥和弯头双锥上的气动力系数、压力分布和油流图案,并且把它们作了比较。其攻角,以后锥轴为基准,从0°变到40°。在马赫数10下对装在底部的配平翼的偏折角对气动力特性的影响进行了研究。通过在马赫数为6的空气流中及马赫数为6的四氟化碳(CF_4)气流中试验这两种双锥模型,模拟了真实气体对气动力系数、压力分布以及激波脱体距离的影响。(其密度比对空气来说是5.3,对CF_4来说是12)。在具有设想的重心和配平翼外形下,当攻角大于零度时,同轴双锥是稳定的,但无法配平。在攻角从零度到23°时,弯头双锥上的配平翼产生了一个稳定而又配平的构形。观察到密度比对气动力系数、压力分布和激波脱体距离有重大影响。
The aerodynamic coefficients, pressure distributions and oil flow patterns on the 13 ° / 7 ° coaxially conic and elbow double cones of the ball were measured in airflows at Mach 6 and 10 and compared with them . Its angle of attack, after the cone axis as a benchmark, from 0 ° to 40 °. The influence of the deflection angle of the trim wing at the bottom on aerodynamic characteristics was investigated at Mach number 10. The two types of double-cone models were tested in a stream of air with a Mach number of 6 and a carbon tetrafluoride (CF 4) stream with a Mach number of 6 to simulate the effect of the real gas on the aerodynamic coefficient, pressure distribution, and shock pick-up distance Impact. (Its density is 5.3 for air and 12 for CF_4). With the assumed center of gravity and trim wing profile, the coaxial double cone is stable but not trimmed when the angle of attack is greater than zero degrees. The trim wing on the double cone of the elbow produces a stable and trim configuration at angles of attack ranging from zero to 23 °. It is observed that the density ratio has a significant effect on the aerodynamic coefficient, pressure distribution and shock pick-up distance.