高速飞行器防热减阻新概念构型的气动性能

提出了一种高速飞行条件下兼具防热减阻的凹腔槽道气动构型，建立了凹腔深宽比为1，槽道高度分别为0、10、20、30、40 mm的凹腔槽道构型，以及槽道入口高度固定为30 mm，出口高度分别为35、40、45、50 mm的扩张型凹腔槽道构型。采用求解Navier-Stokes（N-S）方程方法进行计算，获得了不同算例的鼻锥外壁面热流密度分布以及构型阻力系数的变化情况，分析了凹腔槽道构型参数对气动热与气动力性能的影响。数值结果表明凹腔槽道构型能够达到预期的防热减阻效果。较优构型（槽道进出口高度比为30/50）的防热率与减阻率分别达到40.1%和16.8%。槽道高度越高，减阻效果越好，但防热效率降低。相较于平直型凹腔槽道，扩张型凹腔槽道构型能够在保证防热率不变的情况下显著提升减阻性能。 

Aerodynamic performance of new conceptual configuration of high speed vehicle's heat flux and drag reduction

A heat flux and drag reduction conceptual configuration combining the forward-facing cavity and the channel was proposed with high speed.The ength-to-depth ratio of forward-facing cavity was set as 1.The first series of channel height with 0,10,20,30,40 mm,and the second series of channel entrance height with 30 mm and channel exit height with 35,40,45,50 mm were taken into consideration.The wall heat flux distributions and drag coefficient were extracted from the flow field structures to evaluate the heat flux and drag reduction characteristics via solving Navier-Stokes （N-S） equations.The results showed that the cavity-channel configuration can achieve the expected heat flux and drag reduction.Compared with the baseline blunt cone,the cavity-channel configuration （the channel entrance height to exit height ratio of 30/50） had the optimal but not best heat flux and drag reduction performance within the range considered,and the heat flux and drag reduction rates reached approximately 40.1% and 16.8%,respectively.Higher channel height indicated better the drag reduction,but the heat flux protection effectiveness became weakened.Moreover,higher channel exit height with a constant channel entrance height could enhance the drag reduction effectiveness without any heat flux reduction penalty.