压升规律可控的高超声速内收缩进气道设计方法研究
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摘要
设计高超声速内收缩进气道的核心在于设计优良的基准流场。本文采用有旋特征线理论，研究了一种压缩面压升规律可控的新型轴对称基准流场设计方法，对二次曲线压升规律进行了参数化研究，得到了设计参数对基准流场总体性能的影响规律，并分析了粘性对基准流场流动特征及性能的影响。
基于压升规律可控的轴对称基准流场设计方法，结合流线追踪技术设计了圆形进口内收缩进气道，并进行了数值研究。结果表明，采用新型基准流场的内收缩进气道能较好地保持其基准流场的压升规律，采用压力梯度逐渐增大压升规律的进气道压缩效率较高，流量系数较低，采用压力梯度逐渐减小压升规律的进气道压缩效率较低，但流量系数较高。
为了兼顾进气道的压缩效率和流量系数，探索了三次曲线压升规律，设计了矩形转圆形内收缩进气道，并进行了数值及实验研究。结果表明进气道前缘激波较弱，总压恢复较高，并且具有较高的流量系数。风洞实验表明，该进气道在Ma6、4度攻角状态总压恢复为0.45，增压比为41.2，至少可抗200倍来流静压的反压。
基于三次曲线压升规律的研究，提出了反正切曲线压升规律，研究了这种压升规律基准流场特性及压升规律各个系数对基准流场性能的影响。对采用该规律的圆形进口内收缩进气道进行的数值研究表明，进气道前缘激波较弱，内收缩比较小，在设计点和非设计点进气道均具有较高的压缩效率和流量捕获特性。之后采用该压升规律设计了带斜楔前体的矩形转圆形内收缩进气道，并进行了数值和实验研究。数值研究表明，在Ma4～Ma7范围内，进气道具有较高的压缩效率、较高的流量系数和良好的攻角特性。风洞实验结果表明，设计点和非设计点，进气道顶板沿程压力分布均具有反正切曲线的特征，设计点Ma6状态进气道总压恢复为0.517，增压比为37.0。在Ma5、8度攻角进行的起动特性实验表明，无放气状态，进气道在风洞中不能正常起动。通过在顶板压缩面上的激波与附面层相互作用区域放气可使进气道顺利起动，起动后放气量约为唇口封闭截面流量的1.2%。
为减弱进气道内压段较强的激波与附面层相互作用，通过改变中心体形状，设计了新型轴对称基准流场，反射激波强度显著降低，压缩效率明显提高。对采用该基准流场的圆形流管内收缩进气道研究表明，进气道设计点和接力点肩点附近激波与附面层相互作用明显减弱，流场结构优于传统内收缩进气道，压缩效率明显提高，同时起动性能改善。对采用该基准流场的矩形转圆形内收缩进气道进行了数值模拟和风洞实验。数值研究表明，进气道内压段唇口激波与附面层相互作用较弱，流场结构较好。实验结果表明，在Ma6、4度攻角状态，进气道总压恢复为0.518，增压比为52。在Ma5、8度攻角状态，在顶板上开两道很小的放气槽后进气道可顺利起动，起动后放气量约为1.1%。
最后，初步设计了腹下进气的乘波前体、矩形转圆形内收缩进气道一体化构型，数值研究表明，设计点一体化进气系统前缘激波较好的贴在前缘线上，乘波性能良好，前体产生的三维流场导致进气道流场不再对称。此外，采用乘波前体和类水滴形高超声速内收缩进气道设计了两侧进气布局的进气系统。数值研究表明，前体外流场和进气道内流场在高马赫数下基本独立，低马赫数下前体前缘激波面和进气道前缘激波面耦合。由于没有前体附面层的影响，进气道流场结构较好，压缩效率较高，进气系统升阻比几乎不随来流马赫数变化。
The key of designing hypersonic inward turning inlet is to design its basic flowfield. A new kindof design methodology of axisymmetric basic flowfield with controlled wall pressure rise law isinvestigated using the rotational method of characteristics. Parametric study is performed to obtain thelaws of overall performance variation with design parameters of basic flowfield using pressure riselaw of two-order curve, and the effect of viscosity is also studied.
With this design methodology of basic flowfield, in combination with streamline tracingtechnique, a circular inward turning inlet is designed and simulated numerically. Results show that theinward turning inlet can maintain the same law of pressure rise as its basic flowfield. The inlet withpressure rise law of pressure gradient increasing has the high compression efficiency, but low masscapture ratio, and the inlet with pressure rise law of pressure gradient decreasing is opposite.
With basic flowfield based on the pressure rise law of three order curve, a hypersonic inwardturning inlet with rectangular to circular shape transition is designed and investigated with numericalsimulation and experimental method. The numerical results indicate that this inlet has weak leadingshock wave, and good overall performance. And the experimental results show that the inlet’s totalpressure recovery is0.45, it can generate a compression ratio of41.2and withstand a back pressureratio of200relative to the tunnel static pressure at Mach6with angle of attack of4degree.
According to the investigation of three order curve law of pressure rise, the pressure rise law oftarc tangent curve is proposed. Numerical simulation is performed to study the performance ofaxisymmetric basic flowfield with this kind of pressure rise law. This curve has three parameters,whose effects on the performance parameters such as total pressure recovery, static pressure ratio,contraction ratio and internal contraction ratio was studied. Then, a circular inward turning inlet withthis basic flowfield is designed and numerically simulated to get the flow characteristics and totalperformance. The result shows this inlet has weak leading shock wave and small internal contractionratio, as well as high mass capture ratio and compression efficiency at both on-design point andoff-design conditions. In addition, a hypersonic inward turning inlet with rectangular to circular shapetransition integrated to a wedge forebody was designed and studied by numerical simulation, andtested in a hypersonic wind tunnel. Numerical results indicate that this inlet has high total pressurerecovery, mass capture ratio and good performance with angle of attack from Mach4to Mach7.Wind tunnel test data turn out that this inlet has similar pressure rise law as arc tangent curve, a totalpressure recovery of0.517, and a compression ratio of37relative to tunnel static pressure at Mach6. The starting performance with and without bleeding on top wall in the internal compression section is
studied at Mach5,8degree angle of attack. The results indicate that the inlet can not start withoutbleeding. But when the bleed slots in the zone where shock wave and boundary layer interaction ontop wall were open, the inlet can start with about1.2%mass flow rate of the flow entering the cowlclosure section lost.
An innovative basic flowfield with controlled centre body is designed and studied, which ishelpful to weak the reflection shock wave and increase the compression efficiency. A circular inwardturning inlet using the new basic flowfiled is designed and numerically studied. The results indicatethe new inlet has weaker cowl shock wave/boundary layer interaction, better flowfield, highercompression efficiency, and better starting performance than the previous inward turning inlets. Basedon this new kind of baisic flowfield, a hypersonic inward turning inlet with rectangular to circularshape transition is designed and studied by numerical simulation, and tested in a hypersonic windtunnel at Mach6and Mach5. The inlet has a total pressure recovery of0.518, a compression ratio of52at Mach6with4degree angle of attack, and can start with about1.2%of the flow entering thecowl closure section lost at Mach5with8degree angle of attack.
An inlet system with waveride forebody and hypogastric hypersonic inward turning inlets withrectangular to circular shape transition is designed and numerically simulated, the leading shock waveattaches to the leading edge of forebody at design point, the three dimensional flowfield produced bythe forebody make the inlets’ flowfield be asymmetric. Then another inlet system for hypersonicaircraft with waverider forebody and lateral hypersonic inward turning inlets is designed andnumerically simulated. The results indicate that, at high Mach numbers the external flowfiled offorebody is independent from the inlet’s internal flowfiled, but at low Mach numbers the shock wavesfrom forebody leading edge and inlet leading edge are coupling. Because the boundary layer does notenter the inlets, and then interactions of shock wave and boundary layer are weak, there is noseparation in the flowfield, which is helpful for improving compression efficiency, the L/D of the inletsystem nearly does not change with the free stream Mach number.
基于压升规律可控的轴对称基准流场设计方法，结合流线追踪技术设计了圆形进口内收缩进气道，并进行了数值研究。结果表明，采用新型基准流场的内收缩进气道能较好地保持其基准流场的压升规律，采用压力梯度逐渐增大压升规律的进气道压缩效率较高，流量系数较低，采用压力梯度逐渐减小压升规律的进气道压缩效率较低，但流量系数较高。
为了兼顾进气道的压缩效率和流量系数，探索了三次曲线压升规律，设计了矩形转圆形内收缩进气道，并进行了数值及实验研究。结果表明进气道前缘激波较弱，总压恢复较高，并且具有较高的流量系数。风洞实验表明，该进气道在Ma6、4度攻角状态总压恢复为0.45，增压比为41.2，至少可抗200倍来流静压的反压。
基于三次曲线压升规律的研究，提出了反正切曲线压升规律，研究了这种压升规律基准流场特性及压升规律各个系数对基准流场性能的影响。对采用该规律的圆形进口内收缩进气道进行的数值研究表明，进气道前缘激波较弱，内收缩比较小，在设计点和非设计点进气道均具有较高的压缩效率和流量捕获特性。之后采用该压升规律设计了带斜楔前体的矩形转圆形内收缩进气道，并进行了数值和实验研究。数值研究表明，在Ma4～Ma7范围内，进气道具有较高的压缩效率、较高的流量系数和良好的攻角特性。风洞实验结果表明，设计点和非设计点，进气道顶板沿程压力分布均具有反正切曲线的特征，设计点Ma6状态进气道总压恢复为0.517，增压比为37.0。在Ma5、8度攻角进行的起动特性实验表明，无放气状态，进气道在风洞中不能正常起动。通过在顶板压缩面上的激波与附面层相互作用区域放气可使进气道顺利起动，起动后放气量约为唇口封闭截面流量的1.2%。
为减弱进气道内压段较强的激波与附面层相互作用，通过改变中心体形状，设计了新型轴对称基准流场，反射激波强度显著降低，压缩效率明显提高。对采用该基准流场的圆形流管内收缩进气道研究表明，进气道设计点和接力点肩点附近激波与附面层相互作用明显减弱，流场结构优于传统内收缩进气道，压缩效率明显提高，同时起动性能改善。对采用该基准流场的矩形转圆形内收缩进气道进行了数值模拟和风洞实验。数值研究表明，进气道内压段唇口激波与附面层相互作用较弱，流场结构较好。实验结果表明，在Ma6、4度攻角状态，进气道总压恢复为0.518，增压比为52。在Ma5、8度攻角状态，在顶板上开两道很小的放气槽后进气道可顺利起动，起动后放气量约为1.1%。
最后，初步设计了腹下进气的乘波前体、矩形转圆形内收缩进气道一体化构型，数值研究表明，设计点一体化进气系统前缘激波较好的贴在前缘线上，乘波性能良好，前体产生的三维流场导致进气道流场不再对称。此外，采用乘波前体和类水滴形高超声速内收缩进气道设计了两侧进气布局的进气系统。数值研究表明，前体外流场和进气道内流场在高马赫数下基本独立，低马赫数下前体前缘激波面和进气道前缘激波面耦合。由于没有前体附面层的影响，进气道流场结构较好，压缩效率较高，进气系统升阻比几乎不随来流马赫数变化。
The key of designing hypersonic inward turning inlet is to design its basic flowfield. A new kindof design methodology of axisymmetric basic flowfield with controlled wall pressure rise law isinvestigated using the rotational method of characteristics. Parametric study is performed to obtain thelaws of overall performance variation with design parameters of basic flowfield using pressure riselaw of two-order curve, and the effect of viscosity is also studied.
With this design methodology of basic flowfield, in combination with streamline tracingtechnique, a circular inward turning inlet is designed and simulated numerically. Results show that theinward turning inlet can maintain the same law of pressure rise as its basic flowfield. The inlet withpressure rise law of pressure gradient increasing has the high compression efficiency, but low masscapture ratio, and the inlet with pressure rise law of pressure gradient decreasing is opposite.
With basic flowfield based on the pressure rise law of three order curve, a hypersonic inwardturning inlet with rectangular to circular shape transition is designed and investigated with numericalsimulation and experimental method. The numerical results indicate that this inlet has weak leadingshock wave, and good overall performance. And the experimental results show that the inlet’s totalpressure recovery is0.45, it can generate a compression ratio of41.2and withstand a back pressureratio of200relative to the tunnel static pressure at Mach6with angle of attack of4degree.
According to the investigation of three order curve law of pressure rise, the pressure rise law oftarc tangent curve is proposed. Numerical simulation is performed to study the performance ofaxisymmetric basic flowfield with this kind of pressure rise law. This curve has three parameters,whose effects on the performance parameters such as total pressure recovery, static pressure ratio,contraction ratio and internal contraction ratio was studied. Then, a circular inward turning inlet withthis basic flowfield is designed and numerically simulated to get the flow characteristics and totalperformance. The result shows this inlet has weak leading shock wave and small internal contractionratio, as well as high mass capture ratio and compression efficiency at both on-design point andoff-design conditions. In addition, a hypersonic inward turning inlet with rectangular to circular shapetransition integrated to a wedge forebody was designed and studied by numerical simulation, andtested in a hypersonic wind tunnel. Numerical results indicate that this inlet has high total pressurerecovery, mass capture ratio and good performance with angle of attack from Mach4to Mach7.Wind tunnel test data turn out that this inlet has similar pressure rise law as arc tangent curve, a totalpressure recovery of0.517, and a compression ratio of37relative to tunnel static pressure at Mach6. The starting performance with and without bleeding on top wall in the internal compression section is
studied at Mach5,8degree angle of attack. The results indicate that the inlet can not start withoutbleeding. But when the bleed slots in the zone where shock wave and boundary layer interaction ontop wall were open, the inlet can start with about1.2%mass flow rate of the flow entering the cowlclosure section lost.
An innovative basic flowfield with controlled centre body is designed and studied, which ishelpful to weak the reflection shock wave and increase the compression efficiency. A circular inwardturning inlet using the new basic flowfiled is designed and numerically studied. The results indicatethe new inlet has weaker cowl shock wave/boundary layer interaction, better flowfield, highercompression efficiency, and better starting performance than the previous inward turning inlets. Basedon this new kind of baisic flowfield, a hypersonic inward turning inlet with rectangular to circularshape transition is designed and studied by numerical simulation, and tested in a hypersonic windtunnel at Mach6and Mach5. The inlet has a total pressure recovery of0.518, a compression ratio of52at Mach6with4degree angle of attack, and can start with about1.2%of the flow entering thecowl closure section lost at Mach5with8degree angle of attack.
An inlet system with waveride forebody and hypogastric hypersonic inward turning inlets withrectangular to circular shape transition is designed and numerically simulated, the leading shock waveattaches to the leading edge of forebody at design point, the three dimensional flowfield produced bythe forebody make the inlets’ flowfield be asymmetric. Then another inlet system for hypersonicaircraft with waverider forebody and lateral hypersonic inward turning inlets is designed andnumerically simulated. The results indicate that, at high Mach numbers the external flowfiled offorebody is independent from the inlet’s internal flowfiled, but at low Mach numbers the shock wavesfrom forebody leading edge and inlet leading edge are coupling. Because the boundary layer does notenter the inlets, and then interactions of shock wave and boundary layer are weak, there is noseparation in the flowfield, which is helpful for improving compression efficiency, the L/D of the inletsystem nearly does not change with the free stream Mach number.
引文
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[78] Milinda V. Suraweera and Michael K. Smart，Shock Tunnel Experiments with a Mach12REST Scramjet at Off-Design Conditions[R]， AIAA2008-100.
[79] James.C. Turner and Michael.K. Smart，Application of radical farming to a3-D scramjet atMach8[R]. AIAA2008-101.
[80] Rowan J. Gollan and Michael K. Smart, Design of Modular, Shape-transitioning Inlets for aConical Hypersonic Vehicle[R]. AIAA-2010-0940.
[81] Trent M. Taylor，David VanWie，Performance Analysis of Hypersonic Shape-ChangingInlets，Derived from Morphing Streamline Traced Flowpaths[R]. AIAA2008-2635.
[82] Yancheng You, Dewang Liang, Cross Section Controllable Hypersonic Inlet Design UsingStreamline Tracing and Osculating Axisymmetric Concepts[R]. AIAA2007-5379.
[83] Yancheng You, Dewang Liang, Ke Cai, Numerical Research of Three-Dimensional SectionsControllable Internal Waverider Hypersonic Inlet[R]. AIAA2008-4708.
[84] Yancheng You, Dewang Liang, Rongwei Guo, High Enthalpy Wind Tunnel Tests ofThree-Dimensional Section Controllable Internal Waverider Hypersonic Inlet[R]. AIAA2009-31.
[85] Ryan P. Starkey and Mark J. Lewis. Simple analytical model for parametric studies ofhypersonic waveriders[R]. AIAA-98-1616.
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