锥柱旋成体跨音速脉动压力风洞试验研究

Wind tunnel test research on fluctuating pressure of cone-cylinder rotated body

为研究同时具有"锥—柱"和"柱—裙"拐角的飞行器跨音速脉动压力载荷特征与分布规律,在NF-6风洞中对具有该特点的某旋成体模型开展了试验研究,获得了脉动压力总声压级沿模型纵向的分布规律,及其随来流Ma数与攻角的变化规律。进而通过调整风洞试验段总压改变Re数,获得了脉动压力总声压级在不同Re下的变化规律。结果表明,当来流Ma数达到0.89时,由于激波振荡使旋成体膨胀拐角处出现较强的脉动压力,攻角的增加使脉动压力总声压级有所减小,而Re数的增加使得脉动压力总声压级有所增大,但这种趋势随着来流Ma数接近于1而逐渐减弱。对旋成体跨音速脉动压力载荷的试验研究,为飞行器载荷环境设计提供了依据。

In order to study the characteristics and distribution regularity of spacecraft transonic fluctuating pressure,which the cone-cylinder and cylinder-flare corners are existed in the spacecraft together,test research is performed in NF-6 wind tunnel according to the rotated body model who has the specialty above.The axial distributing rules of the overall sound pressure level（OASPL） of the fluctuating pressure are acquired as well as the varying rules with the Ma number and attack angle.Subsequently,the Re number is changed by adjusting the total pressure of the test section in the wind tunnel and the varying rule with different Re number of the fluctuating pressure is acquired.According to the results,a strong fluctuating pressure is generated on the expansible angle of the body due to shock wave oscillation and The OASPL of the fluctuating pressure decreases with the increase of the attack angle.With the increase of the Re number,the OASPL of the fluctuating pressure is enhanced.However,this trend is decreasing with the Ma number closing to 1 gradually.The test research of the transonic fluctuating pressure provides some references on spacecraft loads and environments design.