ScholarWorks@Gyeongsang National University: Myong, Rho Shin

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Myong, Rho Shin (명노신)

대학원 (기계항공우주공학부)

Research Area

Tel 0557721645
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Keyword

CFD:16||전산유체역학:12||전산유체역학(CFD):10||Computational Fluid Dynamics:9||전산유체역학(Computational Fluid Dynamics):9||Discontinuous Galerkin:7||Aircraft icing:6||적외선 신호:6||CFD(전산유체역학):5||Freely Spinning Tailfin(자유회전 테일핀):4||플룸 유동장:4||Kinetic theory:4||Ice Accretion:4||공력 소음(Aerodynamic Noise):4||Rotorcraft:3||Dusty gas:3||Plume flow field:3||Nonlinear coupled constitutive relations:3||Discontinuous Galerkin (DG):3||Ice accretion:3||Radar Cross Section:3||Rarefied and microscale gases:3||Infrared Signature:3||discontinuous Galerkin method:3||Infrared signature:3||Airworthiness Certification:3||Shockvortex interaction:2||복합 열전달(Conjugate Heat Transfer):2||Collection Efficiency(축적율):2||Airfoil Icing:2||Lightning:2||Slip and jump conditions:2||Aerodynamics:2||rarefied gases:2||Composite:2||Aircraft:2||액적충돌 (Droplet Impingement):2||액적충돌(Droplet Impingement):2||Electrothermal antiicing system:2||CanardControlled Missile(커나드 조종 미사일):2||shock waves:2||열유동장(Thermal Flow Field):2||Aircraft Icing:2||Computational Aeroacoustics:2||Panel Method (패널기법):2||유한요소법):2||유한체적법 (Finite Volume Method):2||Critical icing condition:2||Hypersonics:2||Thermal Flow Field:2||Thermal Flowfield:2||Aspect Ratio:2||Eulerian:2||Thrust Measurement Sytem(추력측정장치):2||Lockon Range:2||적외선 신호(Infrared Signature):2||EulerianEulerian:2||Physical Optics:2||격자 볼츠만 법:2||격자 볼츠만 법(Lattice Boltzmann Method):2||Truncated Flapped Airfoil(절단 플랩 익형):2||전산유체역학 (CFD):2||Twofluid model:2||결빙 증식:2||결빙 증식(Ice Accretion):2||결빙 풍동시험:2||MVD(평균액적크기):2||결빙증식 (Ice Accretion):2||결빙증식(Ice Accretion):2||UAV nozzle:2||Computational Fluid Dynamics(전산유체역학):2||추력(Thrust):2||Unmanned Combat Air Vehicle(무인전투기):2||Ice Protection System:2||Exhaust Nozzle:2||공력음향학(Aeroacoustics):2||Urban Air Mobility:2||DSMC:2||Computational fluid dynamics:2||Icing Wind Tunnel Test:2||Vacuum Condition(진공 조건):2||Radar Cross Section (RCS:2||Meta model:2||항공기 결빙 (Aircraft Icing):2||항공기 결빙(Aircraft Icing):2||Icing Wind Tunnel Test(결빙 풍동 시험):2||Viscous Loss(점성 손실):2||Finite Element Method (FEM:2||Volume Spline Interpolation (3차원보간법):2||Design Optimization:2||MicroSatellite(마이크로 인공위성):2||Diatomic and polyatomic gases:2||Micronozzle(마이크로 노즐):2||다상유동(Multiphase Flow):2||FluidStructure Interaction(유체구조 통합):2||Conjugate Heat Transfer:2||Infrared Signature Prediction(적외선 신호 예측):2||대기 투과율:2||Roll Lockin Phenomenon(회전잠김 현상):2||RollRate(회전율):2||도심 항공 모빌리티(Urban Air Mobility):2||chemical oxygeniodine laser (COIL):2||Missile DATCOM:2||constitutive relations:2||Direct simulation Monte Carlo:2||레이더 포착면적):2||로터기체 상호작용(RotorAirframe Interaction):2||Multielement Airfoil:2||Kriging Surrogate Model:2||Discontinuous Galerkin method:2||LWC(액적량):2||Geometrical Optics:2||무인항공기 노즐:2||Multidisciplinary Design (다분야 통합설계):2||SemiEmpirical Method(반실험적 기법):2||interleaved jet:2||Air intake:2||Grid Deformation(격자 변형):2||CSD(전산구조역학):2||Lattice Boltzmann Method:2||배기노즐:2||Cold Gas Propulsion System(냉가스 추진장치):2||Heating power:1||Helicopter:1||High Intensity Radiated Field(고강도전자기장):1||High Temperature Reacting Gas:1||Hovering Flight:1||Hub Fairing:1||Hybrid Method:1||Hydrophobicity:1||Hypersonic reentry vehicles:1||IR Signature:1||IR Signature Suppression:1||IR Suppression:1||Ice Accretion(결빙 증식):1||Ice Detection System:1||Ice Shedding:1||Ice accretion and shedding:1||Ice protection system:1||Icing Delay Time:1||Icing Wind Tunnel Test(결빙풍동시험):1||Induced Environment:1||Infrared Emissivity:1||Infrared Signal:1||Infrared signal:1||Infrared signature (IR):1||Inhomogeneous boundary condition:1||Iterative Technique:1||Iterative technique:1||Jet Engine:1||LES(Large Eddy Simulation):1||LangmuirMaxwell:1||LangmuirSmoluchowski:1||Largeeddy simulation:1||Lattice Boltzmann Equation:1||LatticeBoltzmann Method:1||LatticeBoltzmann Method (격자 볼츠만 법):1||Latticeboltzman method:1||Lethal Envelope:1||Lightning Effect:1||Lightning Indirect Effects:1||Lightning Protection System(LPS):1||Lightning Protection Systems(낙뢰 보호장치):1||Lightning Strike:1||Lightning Strike Zones(낙뢰 피격부위):1||Lightning Strike(낙뢰 피격):1||Lightning direct effects:1||Lightning protection system:1||Lightning test:1||Lightning zoning:1||Linear quadratic regulator:1||Local stability:1||Lunar Module Descent Engine:1||Lunar landing:1||MILSTD810G Change 1:1||Mach disk location:1||Mach number:1||Mach reflection:1||Machine Learning:1||Manned Unmanned Teaming:1||Maximum Range(최대사거리):1||Mechanical properties:1||Meta Aramid Resin:1||Micro Turbo Jet Engine:1||Micro Turbojet Engine:1||Micro gas turbine:1||Microfluidics:1||Microscale and rarefied gas:1||Micro/nano channel:1||Microscale Gases:1||Microscale and nanoscale gases:1||Microscale shockvortex interaction:1||Microscale/nanoscale heat transport:1||Missile Range:1||Mission System:1||Mixed discontinuous Galerkin method:1||Multielement airfoil:1||Multielement iced airfoil:1||Multiphase flow:1||Multiphysics simulation:1||Multiscale method:1||Multidimensional problem:1||Multifunctional deicing composite:1||Multiphase Model:1||Multiphysics deicing simulation:1||Multiphysics simulation:1||Narrowband model:1||Natural Environment:1||Nearcontinuum flow:1||Neural Network(신경회로망):1||Neural dynamic inversion:1||New boundary conditions:1||Nickelplated carbon fabric:1||NonNavierFourier laws:1||Nonlinear vortex lattice method:1||Nusselt number:1||OpenFOAM:1||Optimum Design:1||Overset Method:1||POD):1||Parachute System:1||Parallel computation:1||Particle Injection:1||Personal Air Vehicle:1||Personal Air Vehicle(개인용 항공기):1||Phase change:1||Physical Optics(PO):1||PitotTube(피토관):1||Plume Flow Field:1||Plumesurface interaction:1||Pressureless gas dynamics equations:1||Proprotor blade:1||Proper Orthogonal Decomposition(적합직교분해:1||Proper orthogonal decomposition:1||RANS (Reynolds Averaged NavierStokes):1||RSM(반응면 기법):1||Radar Absorbing Material:1||Radar Cross Section(RCS):1||Radar cross section (RCS):1||Rader Cross Section:1||Range Extension(사거리연장):1||Rarefaction:1||Rarefied and microscale gas:1||Rarefied and microscale gas flows:1||Rarefied gases:1||Reentry Vehicle:1||Reentry vehicle:1||Relaxation model:1||Reynolds Number Effects:1||Ridge Iced Airfoil:1||Rossiter Formula:1||Rotor Aerodynamic Performance:1||Rotor aerodynamics:1||Rotor blade:1||Rotor wake:1||SCG:1||Scaled Conjugate Gradient:1||Scaling:1||Scaling Method(스케일링 기법):1||Schlieren visualization:1||Secondorder BoltzmannCurtiss:1||Secondorder constitutive models:1||Sensitivity Analysis:1||Severe icing:1||Shape Optimization(형상최적화):1||Shapes of nozzle:1||Shock structure:1||Simulation:1||Simulation results:1||Single Serpentine Nozzle:1||Skin Friction Drag:1||Slip Models:1||Slip gas flows:1||Stagnation Temperature:1||Superparallel performance:1||Supercooled large droplet:1||Supercooled large droplet (SLD):1||Supersonic Aircraft:1||Supersonic multiphase flow:1||Surface erosion:1||Survivability:1||Sustainable aircraft:1||Tailoring:1||Thermal Creep:1||Thermal properties:1||Thin films:1||Timestep:1||Trajectory Analysis:1||Transition Reynolds Number:1||Turbulence Model:1||Twophase flow:1||Twotemperature formulation:1||UCAV:1||Unmanned Combat Aerial Vehicle:1||Unmanned aerial vehicle:1||Unmanned combat aerial vehicle (UCAV):1||Unsteady formulation:1||Urban Air Mobility (도심항공모빌리티):1||Urban Air Mobility(도심항공교통):1||Urban air mobility (UAM) aircraft:1||Vacuum:1||Varying Mass:1||Verification:1||Vertiport (버티포트):1||Vibrational nonequilibrium:1||Viscous vortex particle method:1||Vortex methods:1||Vortex particle method (VPM) · Fast multipole method (FMM) · Nonlinear vortex lattice method (NVLM) · Vortex methods · Wake dynamics · Multirotor:1||Vortex shedding:1||Wake dynamics:1||Wall Heat Flux Specified Boundary Condition:1||Wall heat flux:1||Weapon Engagement Zone:1||Wind Turbine Blade:1||Wires:1||adsorption at solid surfaces:1||asymmetric:1||cable bundle:1||cavity flows:1||constitutive model:1||coupled thermalelectrical approach:1||diatomic gases:1||doublewedge:1||eVTOL:1||eVTOL (전기추진 수직이착륙기):1||flowfield:1||forward flight(전진비행):1||fuel vapour ignition:1||hot spot formation:1||hovering flight(제자리비행):1||hyperbolic system:1||hypersonic:1||hypersonic flow:1||lightning:1||lightning indirect effect:1||limiters:1||moment method:1||nonFourier law:1||nonclassical constitutive laws:1||nonlinear coupled constitutive relations:1||numerical simulation:1||numerical study:1||oscillation:1||particleladen underexpanded jets:1||rarefied gas:1||rarefied gas flows:1||regular reflection:1||reset sampling:1||rotorcraft:1||shock:1||shock interaction:1||shock structure:1||slip and jump conditions:1||small signal gain:1||small signal gains:1||statistical error:1||steady state detection:1||transition:1||type II error:1||unsteady structures:1||verification:1||without buffer gas:1||가로세로비:1||감항인증:1||격자 볼츠만 방법:1||격자볼츠만 법(LatticeBoltzmann Method):1||결빙 궤적(Ice Trajectory):1||결빙 보호 장치(Ice Protection System):1||결빙 지연 시간:1||결빙증식:1||결빙풍동(Icing Wind Tunnel):1||고속 유동(Highspeed Flow):1||고온반응기체:1||공기 흡입구:1||공기흡입구(Air Intake):1||공력 상호작용:1||공력 소음:1||공력특성(Aerodynamic Characteristics):1||과냉각 대형 액적:1||구리입자:1||궤적 분석:1||기하광학법:1||나비에스톡스(NavierStokes):1||낙뢰 영향:1||낙뢰 피격:1||낙뢰보호시스템:1||낙하산 시스템:1||난류모델:1||날개요소 운동량 기법:1||노즐 배기가스(Nozzle Exhaust Plume):1||노즐 형상 최적화(Nozzle Shape Optimization):1||누설 유동(Leakage Flow):1||다물리 해석(Multiphysics Analysis):1||다상 모델(Multiphase Model):1||다상모델:1||단일 S형 노즐:1||대 와류 모사 (Large Eddy Simulation):1||대기 자료 시스템(Air Data System):1||대기 자료 프로브(Air Data Probe):1||대기자료 시스템:1||대기자료계통):1||덕티드 팬(Ducted Fan):1||도심 항공 모빌리티:1||도심항공교통:1||동축 반전 프로펠러:1||레이다 반사 면적(Radar Cross Section):1||레이더 포착 면적:1||레이더 포착면적:1||로켓 노즐 설계(Rocket Nozzle Design):1||로터 공력성능 (Rotor Aerodynamic Performance):1||로터공력성능:1||마이크로 터보제트 엔진:1||마이크로 터보제트엔진:1||막힘(Blockage):1||메타 아라미드 수지:1||무인 전투기(Unmanned Combat Aerial Vehicle):1||무인기:1||무인전투기 노즐(UCAV nozzle):1||물 분사(Water Mist):1||물리광학:1||물리광학법:1||방빙:1||방빙장치:1||방열해석(Cooling Analysis):1||배기 플룸(Exhaust Plume):1||벽에어포일 간섭(WallAirfoil interference):1||보정 기법(Calibration Method):1||복합열전달:1||복합재:1||분산전기추진:1||비정렬 격자(Unstructured Grid):1||비정상유동(Unsteady Flow):1||소수성:1||소형 결빙 풍동(Small Scale Icing Wind Tunnel):1||스케일링:1||시뮬레이션:1||싸이클해석:1||압축성 유동:1||액적 충돌:1||엔진성능:1||열 유동장:1||열유동장:1||열유동장(Thermal Flowfield):1||오일러리안(Eulerian):1||유무인 복합 운영체계:1||유한체적법(Finite Volume Method):1||입자 분사:1||자유회전 테일핀(Freely Spinning Tailfin):1||재진입 비행체:1||재진입 비행체(Reentry Vehicle):1||적외선 방사율:1||적외선 신호 저감(IR Signature Suppression):1||적외선 신호(IR Signature):1||적외선 저감:1||전기추진 수직이착륙기:1||전산 유체 역학(CFD):1||전산 유체역학(CFD):1||전산공력소음:1||전산공력음향학(Computational Aeroacoustics):1||전진비행:1||점성효과(Viscous Effect):1||제자리 비행:1||제트엔진:1||조명탄:1||지면 효과:1||질량 변화:1||천이 영역(Transitional Regime):1||초소형 노즐(Micronozzle):1||초음속 항공기:1||최적설계:1||축소확대 노즐:1||친환경 항공기:1||카나드 설계:1||커나드 조종 미사일(CanardControlled Missile):1||크리깅 근사모델:1||키메라 기법(Chimera Method):1||톱니형 노즐(Serrated Nozzle):1||팁 간격(Tip Clearance):1||편대비행:1||풍동 시험(Wind Tunnel Test):1||풍력블레이드(Wind Turbine Blade):1||풍력터빈 블레이드:1||플루트 노즐(Fluted Nozzle):1||플룸 열유동장(Plume aerothermodynamic flowfiled):1||항공기 결빙:1||항공기 낙뢰:1||항공기 안전성(Aircraft Safety):1||항공기 포착 거리:1||항력 계수(Drag Coefficient):1||항전장비(Avionics Equipment):1||허브 페어링:1||헬리콥터:1||협대역 모델:1||협대역 모델(NarrowBand Model):1||혼합 입자 분사(Mixed Particle Injection):1||회전 잠김 현상(Roll Lockin Phenomena):1||회전익기 결빙(Rotorcraft Icing):1||1D Euler equations:1||후기연소기 장착 터보팬 엔진:1||2D Guidance Fuze:1||2D 탄도수정신관:1||5공 다기능 프로브(FiveHole MultiFunction Probe):1||6 자유도(Six DOF):1||6DoF:1||ADS(Air Data System:1||Actual Transient Level:1||Adaptive Range Genetic Algorithm(적응영역 유전자 알고리즘):1||Adaptive control:1||Adsorption:1||Aeroacoustic (공력소음):1||Aeroacoustics:1||Aerodynamic Heating:1||Aerodynamic Noise:1||Aerodynamic interaction:1||Aerospace Configuration.:1||Aerospace electronics:1||Afterburning Turbofan Engine:1||Air Data System:1||Air Intake:1||Airlaunched Weapon:1||Aircraft Icing(항공기 결빙):1||Aircraft Lightning:1||Aircraft Safety:1||Aircraft Safety(항공기 안전성):1||Aircraft antiicing:1||Airworthiness Certification(감항인증):1||Airworthiness Certification(감항증명):1||Airworthiness certification:1||Altitude Effects:1||Aluminum:1||AntiIcing:1||AntiIcing Equipment:1||Anti/DeIcing:1||Approximate Riemann solver:1||Artificial neural network:1||Atmospheric Icing:1||Atmospheric Transmissivity:1||Atmospheric transmissivity:1||Ballistic Trajectory:1||Blade Element Momentum Method:1||BoltzmannCurtissbased constitutive model:1||Brinkman number:1||Bulk viscosity:1||COIL without buffer:1||Cable Harness:1||Cable Harness(케이블 하네스):1||Cable shielding:1||Canard Controlled Missile:1||Canard Design:1||Carbon fiber composite:1||Cavity Noise:1||Cellsize:1||Chemical reaction:1||Coarray:1||Coaxial Propeller:1||Collection Efficiency(수집율):1||Collection efficiency:1||Component A waveform:1||Component Buildup(부분합성법):1||Composite leading edge:1||Composite wave:1||Compressible Flow:1||Computational Electromagnetics(CEM):1||Computational error:1||Conjugate heat transfer:1||Conservation laws:1||Constitutive equation:1||Constitutive relation:1||Continuum Flow:1||Continuum mechanics:1||Continuumrarefied gas flows:1||Convergence history:1||Convergent Divergent Nozzle:1||Cooling/Heating:1||Copper:1||Copper Particle:1||Coupled electricalthermal:1||Coupling effects:1||Crosssectional shape:1||Curise Missile:1||Cycle Analysis:1||DO160 Section 22:1||Delta shock:1||Diatomic gas:1||Direct Simulation Monte Carlo:1||Discontinuous Galerkin(DG) method:1||Discrete phase model:1||Distributed electric propulsion:1||Double Serpentine Nozzle:1||Double serpentine nozzle:1||Droplet Impingement:1||Droplet impingement:1||Dustvortexlet interaction:1||Electrothermal properties:1||Electrothermal antiicing:1||Electrothermal deicing:1||Empirical Formula:1||Engine Performance:1||Environmental Testing:1||Equipment Transient Design Level(장비 과도 설계수준):1||EulerianEulerian model:1||Exhaust Gas Temperature:1||Exhaust plume:1||Expanded metal foil:1||Finite Element Method:1||Finite Volume Time Domain(FVTD):1||Flare:1||Forcedriven Poiseuille flow:1||Formation Flight:1||Forward Flight:1||Forward flight:1||Freezing Fraction(결빙비):1||Genetic Algorithm(유전자 알고리즘):1||Granular flow:1||Ground Effect:1||Ground Effect (지면 효과):1||Heat Flux:1||Heat flux:1||Heat transfer:1||Heating pad sizing:1||

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