吸气式高超声速飞行器设计中的一些概念研究

南京航空航天大学硕士学位论文吸气式高超声速飞行器设计中的一些概念研究姓名：王志经申请学位级别：硕士专业：流体力学指导教师：程克明20070501iX-43AHARCNHWX-43AiiAbstractThispapermainlyusestechnologyofexperimentandmethodofCFDtomakeanexplorationofaerodynamicperformanceandwholeflowcharacteristicsofhypersonicvehiclewhichissimilartoX-43A.AtHypersonicAerodynamicResearchCenter(HARC)ofNanjingUniversityofAeronauticsandAstronautics(NUAA),weusethehypersonicwind-tunnel(NHW)tostudytheaerodynamicperformanceofthisvehiclemodelatM7andM8.Theexperimentalmainlyconsistsofstaticsurfacepressuremeasurementsandforcemeasurements.BynumericalsimulationatM7,andwithstarting,wesimulatethewholeflowcharacteristicsandanalysistheflowstructureandaerodynamicperformance.Theresultsarevalidatedusingtherelationalexperimentdata,andindicatethemethodofnumericalsimulationhasgreatprecisionwhichcanbeusedinstudyafterward.Furthermore,weanalysistheexternalflowstructureinthree-dimensional,andcontrasttheflowstructuresofdifferentanglesofattack.Moreover,byusingthemethodofnumericalsimulation,wesimulateanewvehiclemodelwhichisinstalledboardsatbothsides.Weanalysistheaerodynamicperformanceandwholeflowcharacteristicsofthisnewvehiclemodel,andcontrastitwithnormalhypersonicvehicle.Theresultsindicatethatafterinstalledtheboardstheliftwillincreasecorrespondingly.Thiswillimprovetheaerodynamicperformanceofthevehicle.Atthesametime,becauseoftheincreaseofthemassininlet,thethrustofthevehiclewillincrease.However,atthesametime,thelossofenergywillaffecttheperformance,andtheweightoftheboardswillalsoaffectstheflightperformanceofthevehicle.Keywords:hypersonic,wholeflowcharacteristics,forebodycompresssurface,inlet,therateofliftanddragv1.1..............................................11.2X-43A..........................................51.3X-43A..............................................52.1NHW..................................................82.2NHW..................................................92.3NHW....................................................92.4Nx-1..............................................132.5Nx-1..........................................132.6Nx-1..................................................142.7NX-1(mm)................................144.1.................................................194.2/................................204.3NX1.....................................234.42...........................244.52...............................254.62.............................254.72...........................264.82...............274.92...................274.10...........................284.1182................294.12................................304.134..........................304.14-3.5.......................314.15...................324.16.....................................334.17-3.5...........334.184..............345.1.........................................365.2...................................37vi5.32.............................375.4.........................385.5.................................395.6...................................39vii2.1.....................................112.1...............................112.2...................................122.3.........................................154.1M0=7.0=2...............265.1.........................................40,()__11151.121[1]2[2]1.12[3]/[20]343[11][12][9,10]36614[13][13,14]Scramjet[21]RBCC3/[2-4,29][51][4,5,6]4//[7,8]4/PropulsionAirframeIntegration,PAI[15]/[15]12/20601985199410NASPLangely[22,23]320082004327X-43A3.66m660mm1.53m1369kg[3]1.251.3ASTP“/”“”RBCC1/1001000[3]1.2X-43A1.3X-43A209019915“”RADUGAD-2IGLA6147.9m3.6mHyper-X/[6]199364840/19941998150[3]9218632931///NASALangely///29/[9,10,14,16,17][18]713X-43ANx-1NHW821NHW2.1-2.3Φ300mm500mm5.0-8.027-59km10s1300mm260mm2.1NHW92.2NHW2.3NHW4M3.5-12/22022.0MPa[34]103.0MPaNHW2×2×2.5m31Φ400mm2600×1200mm2NHWΦ300mmNHWNHW650m30.1Pa[35]NHWPLC2.12.2320.005%100KHzNHWGJB4399-2002112.12.2NHW2.1MP0(MPa)T0(K)H(km)q(kPa)Rel×10-6(1/m)G(kg/s)min0.040292.6450.041.3231.2140.685max1.000350.4526.8533.07622.43515.50min0.060385.1955.390.9580.7800.416max1.000444.6934.1415.96110.2076.42min0.120500.0757.410.9940.7120.377max1.000550.9441.038.2855.0332.93min0.220630.5959.261.0100.6470.298max1.000684.6447.634.5892.5561.282.1MN(MW)T∞(K)P∞(kPa)t(sec.)min0.00348.770.0760.0765max0.96558.411.8901.890min0.04046.970.03870.03876max1.00754.230.6330.633min0.07846.300.0290.0297max0.77251.010.2420.242min0.10145.690.0230.0238max0.51049.610.1020.102122.21DEm0.52M∞-56783Gkg/s0.2915.504P0MPa0.042.05T0K2887006Rel1/m6.47×1052.24×1077Hkm27598ts≥109DMmm12010Vam33211Vvm365022Nx-1X-43A/2.4-2.513Nx-12.65.252.4Nx-12.5Nx-1142.6Nx-12.7NX-1(mm)23Nx-124-B2.71505V±15V2.31).2).SS=(0.46420.4258+20.50.0980.2573)/72=4.5510-3m2zLz=0.257m()LB=0.545m()2.3(kPa)()(mm)052.502510030010001.5105V±15VDCM12×124NHWNx-1X-43A/16Nx-1PAIPropulsionAirframeIntegration311Nx-1a)b)X-43ANx-1563c)17H02Nx-1H03/241671832Nx-1CATIA3.133Nx-1Nx-119Nx-1Nx-1NHW414114.14.1Nx-14.2Nx-1253mm5632H0167OABCD20H0((oABCD4.2/412CFDN-S()0iiuxρ∂=∂(4.1)()ijijjijpuuxxxτρ∂∂∂=−+∂∂∂(4.2)[()]()[()]ieffijeffjijjjTuEpkux