Aeroheating measurements on a reentry capsule model in free-piston shock tunnel HIEST
Aeroheating measurements on a reentry capsule model in free-piston shock tunnel HIEST
复制标题
自由活塞激波风洞中再入舱模型的空气加热测量 HIEST
DOI：
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发表时间：
2010
期刊：
影响因子：
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通讯作者：
K. Miyagi
中科院分区：
文献类型：
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作者：
T. Hideyuki;M. Kodera;K. Tomoyuki;S. Kazuo;Takahashi Masahiro;I. Katsuhiro;K. Miyagi
在自由活塞激波风洞HIEST中测量了Apollo CM模型的气动加热。测量的主要目的是在高焓高雷诺数条件下获得数值代码验证的基准数据。该模型由SUS-304不锈钢制成，直径为250 mm。模型的迎风面装有84个微型同轴铬-康铜热电偶，这些热电偶是日本宇宙航空研究开发机构内部制造的。12个热电偶和两个压阻压力传感器也安装在模型的尾部，并用于确定模型周围的流的建立。在这次试验活动中，测量了迎角为0 °和30 °时的热通量数据。滞止焓和滞止压分别在H 0 = 4 ~ 21 MJ/kg和P0= 14 ~ 58 MPa范围内变化。在全层流边界层和过渡边界层情况下观察了气动加热特性。测量的热通量由斯坦顿数和雷诺数的平方根的乘积归一化，以与其他风洞结果和飞行结果相关联。当滞止焓从H 0 = 4 MJ/kg变化到12 MJ/kg时，归一化热流密度值变化不明显，表明边界层流动通常为层流。然而，在高焓和高雷诺数条件下（H 0超过18 MJ/kg，P0约50 MPa）的射击表明，测量的热流密度比在其他条件下获得的高约40%。
Aeroheating of an Apollo CM model was measured in the free-piston shock tunnel HIEST. The primary purpose of the measurement was to obtain benchmark data for numerical codes validation under high-enthalpy high-Reynolds number conditions. The model was made of SUS-304 stainless steel and had a diameter of 250mm. The windward surface of the model was equipped with 84 miniature co-axial Chromel-Constantan thermocouples that were manufactured in-house at JAXA. Twelve thermocouples and two Piezo-resistive pressure transducers were also mounted aft on the model and were used to determine the establishment of flow around the model. In this test campaign, heat flux data were measured for angles of attack 0o and 30o. Stagnation enthalpy and stagnation pressure were varied from H0=4MJ/kg to 21MJ/kg, and from P0=14MPa to 58MPa, respectively. Aeroheating characteristics were observed with a fully laminar boundary layer and with a transition boundary layer. Measured heat flux was normalized by the product of the Stanton number and the square-root of the Reynolds number for correlation with other wind tunnel results and flight results. The normalized heat flux value did not change remarkably when stagnation enthalpy was changed from H0=4MJ/kg to 12MJ/kg, implying that the boundary layer flow was usually laminar. However, shots under high enthalpy and high Reynolds number conditions (H0 over 18MJ/kg and P0 approximately 50MPa) showed that the measured heat flux was approximately 40% higher than that obtained in other conditions.