[보고서]극초음속 비행체 충격파 및 경계층 예측/제어/회피 기술개발

박수형

보고서 정보

주관연구기관

건국대학교 산학협력단
KonKuk University

연구책임자

박수형

보고서유형

최종보고서

발행국가

대한민국

언어

한국어

발행년월

2016-10

과제시작연도

2015

주관부처

미래창조과학부
Ministry of Science, ICT and Future Planning

등록번호

TRKO201700009401

과제고유번호

1711026140

사업명

우주핵심기술개발사업

DB 구축일자

2017-10-28

키워드

극초음속 비행체.전산유체역학.충격파.압축성 경계층.유동제어.Hypersonic Vehicle.Computational Fluid Dynamics.Shock Wave.Compressible Boundary Layer.Flow Control.

표 Schematic diagram of shock wave and boundary layer around hypersonic vehicle
표 Comparison of rocket and scramjet schematic [1]
표 Schematic diagram of a supersonic flow field in a compression corner [2]
표 Schematic diagram of the flat plate flow field and computational boundaries [2]
표 Schematic diagram showing the computational box and boundary conditions [2]
표 Comparison theoretical and experimental wall pressure distributions [2]
표 JPL Wind Tunnel Models AR-1, 2 [3]
표 Reynolds Number Dependence (Laminar Flow) [3]
표 Aspect Ratio Variation on "Two-dimensional" Model AR-2 with Comparison to "Stovepipe," Model AR-2 [3]
표 Effect of Cooling on Overall Laminar Boundary Layer Separation [3]
표 Reattachment Profiles Adiabatic(left) and Cold(right) wall [3]
표 Surface pressure distribution on the 24° compression corner [4]
표 Preston tube skin friction measurements along the shock boundary-layer interaction [4]
표 Experimental model of the 24° compression corner flow field [4]
표 Flowfield shadowgrams of 8, 16, 20 and 24 deg interactions [5]
표 Selected mean streamwise velocity profiles [5]
표 Free stream conditions [6]
표 Variation of normalized surface pressure and skin friction coefficient [6]
표 Free stream and inflow boundary layer data [7]
표 General grid topology for the 2D compression ramp cases [7]
표 Surface pressure distributions for Princeton series (a) 8°, (b) 16°, (c) 20°, (d) 24° [7]
표 Surface friction distributions for Princeton series (a) 8°, (b) 16°, (c) 20°, (d) 24° [7]
표 RANS calculations of 2-D compression corner [8]
표 Inflow velocity (left) and Reynolds streamwise stress (right) [8]
표 Mean wall pressure(left) skin friction(right) [8]
표 2-D Shock impingement [8]
표 Flow conditions and details of computations [8]
표 Velocity
표 Skin Friction
표 Displacement thickness
표 Velocity
표 RMS Velocity
표 RMS Velocity
표 2-D Expansion-compression corner [8]
표 Instantaneous Schlieren images of (a) the flat-plate boundary layer, (b) 7° centered expansion, and (c) 14° centered expansion [8]
표 Instantaneous FRS visualization of (a) the 7° centered and (b) gradual expansion regions. The white lines indicate the position of the model surface [8]
표 Flow conditions [8]
표 Computation conditions [8]
표 Mean static pressure [8]
표 Mean streamlines [8]
표 Mean velocity [8]
표 Surface pressure [8]
표 Layout of Schlieren system [31]
표 Schlieren images of shock train flow displaying density gradients with respect to the horizontal (upper) and with respect to vertical (lower) [1]
표 Experimental and numerical schlieren image, Ma = 8.1, TW = 760 K, R = 0.5 mm [1]
표 Colour schlieren image of the reference case [1]
표 Schlieren images for different wall temperatures [1]
표 Instantaneous Schlieren image [8]
표 Schematic of experimental set up for shadowgraph visualization [32]
표 Digram of optic path of shadowgraph
표 Shadow graph result (Left : M=3, Right : M=4)[32]
표 Shadowgraph of Model AR-1 at M=4.0, Re=0.89×106 [3]
표 Shadowgraph of Model AR-1 at M=4.0, Re=0.27×106 [3]
표 Diagram of optic path of Holographic Interferogram
표 Oxygen Quenched Photoluminescence
표 Schematic of PSP
표 PSP pressure (AOA=20°)
표 PSP and pressure (AOA=20°)
표 PSP pressure (AOA=30°)
표 PSP and pressure (AOA=30°)
표 Principle of PIV velocity field measurement technique [35]
표 PIV Recordings for the 0° and 25° Models at Mach 2 [38]
표 Diagram of experimental model [37]
표 Camera arrangement (Scheimpflug condition) of SPIV [37]
표 SPIV Results and Schlieren Image of the 0° Model at Mach 2 and ReD = 1.75 × 106 [38]
표 2-D Shock impingement [8]
표 Geometry of the micro-ramps. a Dimensions of a) micro-ramp, b) single-row configuration, c) double-row configuration[39]
표 Conceptual sketch of the perturbed interaction.
표 Mean velocity fields at y/δ = 0.1; u/U∞ (upper), w/U∞ (middle) and v/U∞ (lower); undisturbed interaction (left), disturbed by a single row of micro-ramps (middle), disturbed by staggered array of micro-ramps (right); in the top figures, streamlines and the sonic line are shown.
표 Mean velocity fields at y/δ = 0.6; u/U∞ (upper), w/U∞ (middle) and v/U∞ (lower); undisturbed interaction (left), disturbed by a single row of micro-ramps (middle), disturbed by staggered array of micro-ramps (right); in the top figures, streamlines and the sonic line are shown.
표 The experimental setup. (a) Schematic representation of the installation; (b) the shock generator; (c) the configuration of the micro-ramp array
표 Instantaneous streamwise flow structures: (a) image captured on the median plane of the micro-ramp; (b), and (c) an image pair captured with a delay of 5.5 μs on the 1/6 span location which is expected to be the location of one streamwise vortex core
표 Spanwise flow structure: (a) on the plane with an obliquity of 6.5; (b) on the plane 1.5 mm above the wall.
표 An NPLS image of the wake’s cross section
표 Streamwise flow structures of the SWBLI field: (a) without control over the median plane of the wind tunnel; (b) with control over the median plane of the micro-ramp.
표 Schematic diagram of micro-ramp(left) and micro-vane[41]
표 DP/P0 response surface containing the optimal micro-actuactor array designs
표 Htr response surface containing the optimal micro-actuactor array designs
표 Measurement configuration (dimensions in mm)
표 Boundary layer profiles for undisturbed interaction and passive control
표 Boundary layer profiles at X = 100 mm for the 15 mm long suction cavity
표 Effect of different plate length for Mhole = 0.57
표 Interferograms of the boundary layer development under different suction rates: top - passive control, middle - four hybrid control cases with increasing suction amount towards the bottom picture (CQ = 0.503; 1.237; 2.313; 4.023), bottom - no control
표 Photograph of the SWBLI test section showing the shock generator on top wall and the plasma actuator block on the bottom wall
표 Photograph of the SWBLI tunnel showing the 8 plasma actuators in operation
표 Plan view schematic of PIV experimental arrangement
표 Streamwise velocity profile of various forcing cases on the centerline of an actuator at X* = -0.29 and Xa*= -1.25 (upstream of the SWBLI) using forcing method 1 (all actuators operating in phase)
표 Streamwise velocity maps for the baseline and two forced cases at X* = -0.29 and Xa* = -1.25 (upstream of the SWBLI) using forcing method 1
표 Basic flow features for mesoflap control of SBLI
표 Upstream and downstream flap deflections during an experiment
표 Streamwise variations of a) surface static pressure and b) skin friction downstream of the interaction.
표 Mach number contours for flxed-deflection four-flap cases:a) D1 = 0.25 and D2 = 0.3 (lesser deflection flap case), b) D1 = 0.5 and D2 = 0.4 (greater deflection flap case), c) shadowgraphs for aeroelastic thicker four-flap cases,6 and d) for the thinner four-flap case
표 Experimental setup: a) actuator schematic diagram, b) voltage current trace, and c) pitched/skewed plasma-jet array schematic diagram
표 Schlieren imaging of the separation-scale reduction by the actuator a) without actuation and b) with actuation
표 PLS images showing the separation-scale reduction by the actuator a) without actuation and b) with actuation
표 Force balance for the electrons in the reference frame moving at plasma velocity up, greater than the gas velocity u
표 Upstream plasma column velocity as a function of the magnetic field in experiments compared with analytical model results
표 Schematic of the experimental setup for the study of shockwave - boundary layer interaction and its control
표 Effect of upstream plasma actuation when shockwave is weak and does not induce separation (case 1); a at different magnetic field strengths and b at different current flowing through the actuator
표 Schematic of the experimental setup for the study of shockwave - boundary layer interaction and its control
표 Effect of downstream plasma actuation with shockwave-induced separation (case 2); a at different actuation currents and b at different applied magnetic field strength
표 Layout of Schlieren system[2-1]
표 Difference between Shadowgraph and Schlieren method
표 Schlieren equipments
표 Focal length of the mirror [2-2]
표 Set up the first mirror [2-2]
표 Set up the second mirror [2-2]
표 Effect of Knife-edge location [2-2]
표 Test Arrangement
표 Dual ND:YAG 레이저 제원
표 Configuration of the PIV camera
표 synchronization equipment(up : S/W, down : H/W)
표 Seeding system
표 PIV Software equipments
표 반사로 인한 오차
표 Calibration 이미지
표 PIV raw 이미지
표 Process of Post-processing
표 IR thermography setup on the MAF
표 IR Camera 제원
표 IR Thermography 실험 모습
표 Blackbody calibration
표 Blackbody calibration results
표 K-type thermocouple
표 Comparison with K-type thermocouple
표 Netscanner 9116
표 Comparison of visualization results of for various injection pressure of 3-D model
표 Comparison of visualization results of for various angle of attacks of 3-D model
표 Comparison of visualization results of for various freestream Mach numbers of 3-D model
표 Visualization of interaction with Fin of missle
표 Experiment condition
표 Ogive-Cylinder model
표 Schlieren image of Ogive-Cylinder
표 Shadow image of Ogive-Cylinder
표 Cone-Cylinder model
표 Schlieren image of Cone-Cylinder
표 Shadow image of Cone-Cylinder
표 Theoretical θc-θs-M∞ graph [2-3]
표 Wedge model
표 Schlieren image of Wedge
표 Theoretical θ-β-M∞ graph [3]
표 Experiment condition
표 Plate model
표 Geometry of Plate model
표 Schlieren image of Plate
표 Shadow image of Plate
표 Pressure contour of Plate
표 Pressure distribution of Plate [5]
표 Flow Structure above a delta wing [2-4]
표 Experiment model
표 Delta-wing Geometry
표 Experiment condition
표 PIV Result at x/c = 0.15
표 PIV Result at x/c = 0.85
표 Experiment condition
표 Pressure contour at Free-stream
표 Raw image of Cone-cylinder
표 Pressure contour at Cone-cylinder
표 Raw image of Wedge
표 Pressure contour at Wedge
표 MAF(Model Aerodynamic Facility)
표 Specification of MAF
표 Double Ramp image (left : schlieren, right : shadowgraph)
표 Double Ramp image
표 Pressure in settling chamber
표 Seeding system in settling chamber
표 PIV result (left : seeding in the settling chamber, right : seeding in the pipe)
표 Flat plate model
표 Experiment condition
표 Shadowgraph image(left : Halogen lamp, right : LED lamp)
표 Experiment condition
표 PIV raw image
표 PIV result of flat plate (velocity vector)
표 Velocity profile (chord line 0.3, 0.5, 0.7, 0.9)
표 Mean stream wise velocity
표 Ramp model
표 Experiment condition
표 Shadowgraph image of ramp
표 Experiment condition
표 PIV raw image
표 PIV result of ramp
표 PIV result and shadowgraph image
표 Velocity RMS of ramp
표 Velocity profile (chord line 0.7, 0.9, 1)
표 ACE 극초음속 풍동장비
표 ACE 극초음속 풍동의 작동영역
표 극소 거칠기요소 모델
표 Laminar Boundary Layer (Rex=1.66e6)
표 Tripped Turbulent Boundary Layer (Rex=1.66e6)
표 Schilieren image: Trip flow structure
표 Oil Flow Visualization(Left: No trip, Right: tripped)
표 Oil Flow Visualization:Individual roughness element
표 Schematic of a typical hypersonic vehicle, indicating potential areas for mechanical distortions. Image taken from Pratt and Whitney
표 Schematic of a typical hypersonic vehicle, indicating potential areas for mechanical distortions. Image taken from Pratt and Whitney
표 Graphical representation of the effect of bulk dilatation upon the large-scale structures
표 Summary of the effects of favorable pressure gradient and convex curvature upon the turbulence structure. Note the quenching of the small-scale structures at the boundary layer edge. Taken from Humble et al. (2012)
표 Representative sample of available high-speed rough-wall data [adapted from Bowersox (2007)]
표 Supersonic wind tunnel used in the current study, depicting the settling chamber, nozzle, test section, and diffuser (from left to right). Flow enters from the left
표 Contours of the Mach 4.9 nozzle used in the current study. Flow is from left to right
표 Nominal tunnel operating conditions
표 Schematic of diamond roughness topology
표 Parameters for convex curvature
표 Convex curvature of favorable pressure gradient models. ZPG model not shown here
표 Sample schlieren images, using a gas breakdown-generated spark source. Left column: wall-normal gradient. Right column:streamwise gradient.
표 Overview of PIV technique, describing the five key steps in data collection and processing.
표 Drawing of PIV experimental arrangement, showing the camera system, laser sheet, and test section. Flow is from left to right.
표 PIV experimental parameters
표 PIV seeder used in current experiment.
표 Examples of synthetic vortices, showing the effects of misalignment with the measurement plane
표 Freestream and wall conditions of the baseline flow field
표 Mean velocity profile, compared to a 1/7th power law and the Mach 4.97 DNS data of Duan et al. (2010).
표 Inner-scaled mean velocity, using the van Driest II compressibility transformation
표 Morkovin-scaled velocity fluctuations, compared to existing supersonic studies in literature
표 Reynolds shear stress profiles, scaled by wall shear stress τw
표 Instantaneous velocity field for baseline case, showing a hairpin vortex packet. Individual vortices are identified by subtracting a convective velocity Uc = 0.83Ue. The relation to the sweep/ejection events is shown.
표 격자중심 유한 체적법
표 SGS 모델, DDES 모델 그리고 RANS 모델을 비교한 결과 (RANS와 DDES에 대하여 결과 함께 표시)
표 Configuration of channel
표 Schematic of the rescaling methodology
표 Freestream and inflow boundary layer data for compression cases [7]
표 Grid of 24° ramp
표 Pressure coefficient (8°)
표 Skin friction coefficient (8°)
표 Pressure coefficient (16°)
표 Skin friction coefficient (16°)
표 Pressure contour (16°) SST
표 Pressure contour (16°) S-A
표 Pressure coefficient (20°)
표 Skin friction coefficient (20°)
표 Pressure contour (20°) SST
표 Pressure contour (20°) S-A
표 Pressure coefficient (24°)
표 Skin friction coefficient (24°)
표 Pressure contour (24°) SST
표 Pressure contour (24°) S-A
표 Schematic diagram of a supersonic flow field in a compression corner [2]
표 Pressure contour (24°) SST
표 Inflow conditions
표 Pressure coefficient (24°)
표 Skin friction coefficient (24°)
표 Pressure coefficient (24°)
표 Skin friction coefficient (24°)
표 Pressure coefficient (24°)
표 Skin friction coefficient(24°)
표 Pressure coefficient (24°)
표 Skin friction coefficient (24°)
표 Pressure coefficient (8°)
표 Skin friction coefficient (8°)
표 Pressure coefficient (24°)
표 Skin friction coefficient (24°)
표 Strain contour(Strain1)
표 Vorticity contour(Strain1)
표 Strain contour(Strain3)
표 Vorticity contour(Strain3)
표 Pressure coefficient distributions on the base with compressibility modification
표 U velocity distributions along the centerline with compressibility modification
표 Mach number contour (MLS2 model)
표 Compressibility factor contour (MLS2 model)
표 Primary Reynolds stress profiles with compressibility modification: (a)    , (b)    , (c)    
표 TKE profiles with compressibility modification: (a)  , (b)    , (c)    
표 Axial velocity profile with compressibility modification: (a)    , (b)    , (c)    
표 Relaminarization process [1]
표 Pressure coefficients (sharp leading edge) [4-3]
표 Pressure coefficients (round leading edge) [4-3]
표 Grid of double ramp [4-3]
표 Pressure coefficient (sharp leading edge, Twall=300K)
표 Pressure coefficient (sharp leading edge, Twall=600K)
표 Pressure contour (sharp leading edge, Twall=300K, Transtion)
표 Pressure contour (sharp leading edge, Twall=600K, Transtion)
표 Pressure coefficient (round leading edge, Twall=300K)
표 Pressure coefficient (round leading edge, Twall=600K)
표 Configuration of Experimental Model
표 Surface streak patterns from the 20 and 24 deg compression corner flowfields
표 Grid of 3D compression ramp (24°)
표 Pressure coefficient (ramp 24°)
표 Skin friction coefficient (ramp 24°)
표 Pressure contour (Double Width)
표 Pressure contour (Normal Width)
표 Grid of 24° compression ramp problem
표 Inflow conditions
표 Pressure coefficient (Ramp 8°)
표 Skin friction coefficient (Ramp 8°)
표 Velocity profile (Ramp 8°) X/δ = -1
표 Turbulence eddy viscosity (X/δ = -1, X/δ = 1)
표 Eddy viscosity (S-A, Ramp 8°)
표 Eddy viscosity (k-ω Wilcox, Ramp 8°)
표 Eddy viscosity (k-ω SST, Ramp 8°)
표 Turbulent kinetic energy (k-ω SST, Ramp 8°)
표 Specific dissipation rate (k-ω SST, Ramp 8°)
표 Mean strain rate contour (k-ω SST, Ramp 8°)
표 Pressure coefficient (Ramp 24°)
표 Skin friction coefficient (Ramp 24°)
표 Density contour (S-A, Ramp 24°)
표 Skin friction coefficient (Ramp 24°)
표 Grid of 10° Impinging Shock problem
표 Pressure coefficient (Impinging Shock, 10°)
표 Skin friction coefficient (Impinging Shock, 10°)
표 Density contour (S-A, Fig. 4-77 Density contour (k-ω
표 Skin friction coefficient (Ramp, 24° )
표 Skin friction coefficient (Impinging Shock 10° )

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