3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics CFD Applications and Validations in Aerodynamic Design and Analysis for Missiles Kwang-Seop Lee and Seung-Kyu Hong Agency for Defense Development 3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics 20-21 June 2007 USAF Academy 1/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Outline of Talk • ADD Brief • Numerical Method • Applications - Ogive-cylinder - Boat tail and Spike - VLS Internal Flow - Side jet on body-tail missile • Conclusions 2/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics 3/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics 4/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Military Demarcation Line 5/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics US Navy LOGIR Team Visits to ADD 6/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Cultural Exposure 7/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Cultural Exposure 8/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics ADD Organization ADD Organization Board of Trustees Board of Trustees President President Auditor Auditor Vice President Vice President Staffs Staffs Aircraft/Missile Information/ Aircraft/Missile Information/ Core Technology Ground Systems Defense Systems Naval Systems Core Technology Ground Systems Defense Systems Electro-Warfare Systems Electro-Warfare Systems R&D Center R&D Center Test Center R&D Center R&D Center R&D Center Test Center R&D Center R&D Center R&D Center R&D Center • Missile • E-warfare • EO Sensors • Sensors • Missile • E-warfare • EO Sensors * Proving Ground • Ground Vehicle • Sensors * Proving Ground • Ground Vehicle • C4I • Munitions • Aircraft/UAV • Underwater • C4I • Munitions • Aircraft/UAV • C&B • Underwater • C&B • Aero,G&C • Communication • Prop/Mat’l Weapon • Aero,G&C • Communication • Prop/Mat’l *GV Test Range Weapon *GV Test Range *Aero Sys & Tech * Naval Test *Aero Sys & Tech * Naval Test Test Facilities Test Facilities * R&D Centers * R&D Centers Dual-use Technology Center Dual-use Technology Center System Develop. Division Technology Division MIC (Ministry of Information and Communication) MIC (Ministry of Information and Communication) MOCIE (Ministry of Commerce, Industry and Energy) MOCIE (Ministry of Commerce, Industry and Energy) Test Facilities 9/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics R&D and Acquisition Flow MND • Defense Policy • S&T Policy Acquisition JCS DAPA (Defense Master Plan/ROC) ROC Plan Industry Services ADD Initiation Initiation (ROC/T&E) ADD DTQAA Industry/ Academia/ Institute 10/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics System Development Flow Development Mode Decision Domestic Purchase • Commercial Overseas ROC ROC ROC Preliminary • FMS Initiation Request Decision Study International Devlp. R&D Service JCS MND DAPA Domestic Devlp. Exploratory System Deployment Operation Development Development 11/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Procedure of Aerodynam ic Design Aerodynamic configuration Aerodynamic Characteristics Resize (Aerodynamic coefficients) (Not Allowable) Static Stability (Allowable) Trajectory Simulation Check Aerodynamic Performance Requirements No Satisfed ? Yes Confirm Configuration 12/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Aerodynam ic Analysis • Aerodynam ic coefficients - prediction code - W/ T tests - 6DOF table (trajectory simulation, design of autopilot) • Aerodynam ic load - trim condition - panel code - CFD - structural test • Hinge m om ent - determine hinge axis - hinge moment on hinge axis - W/ T tests for hinge moment 13/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Analysis Tools • Sem i-em pirical prediction tool - for the static and dynamic aerodynamic coefficients - for hinge moment - for aerodynamic loads • Panel m ethod aerodynam ic prediction tool - for aerodynamic coefficients - for aerodynamic loads • Com putational Fluid Dynam ic ( CFD) aerodynam ic prediction tool - in-house code - commercial code 14/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics CFDS Numerical Method • Flux-Difference Splitting Method • Finite Difference Method • 3-D Navier-Stokes Solver • Multiple Blocks • Characteristic Boundary Conditions • Baldwin-Lomax Turbulence Model • Two 1-Equation Models 15/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics CFDS Shock Fixing λ + ε 2 2 λ = λ ≤ ε | | ( ) | | if ε 2 ε = where, constant 10 λ 8 1 λ 1 (m o d ifie d ) 6 AIAA-95-1732-CP 4 2 λ 1 0 • M=8.0 -2 • AOA = 0.0 deg. -4 -6 • Re=1.9x10E8 -8 • Mesh 101x50 -10 3 0 4 0 5 0 6 0 7 0 f ξ c e llin d e xo -d ire c tio n 16/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics CFDS Shock Fixing Mach H=4D 4.00 H=4D 3.71 3.43 3.14 2.86 2.57 2.29 2.00 3.71 1.71 3.64 4.00 1.43 3.92 1.14 4.00 3.64 0.86 0.57 0.29 0.00 0.29 0.56 0.29 0.56 1 . 2.29 6 8 1.12 1.71 1.71 1.12 H=4D H=4D 2.6 2 . 0 5.0 2 . 3 12.0 2.7 16.0 2 . 7 16.7 8.2 Shock Instability Instability Cured 17/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Supersonic Ogive-Cylinder • Mach=3.0 • AoA=10.0 deg. • Re=6x10^6 • Grid=84x65x62 • Baldwin-Lomax Turbulence Model • Degani-Schiff Modification 18/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Supersonic Ogive-Cylinder 4 1.6 Exp.(windward) Exp.(leeward) 3 Present(1st-order) Present Present(2nd-order) EXPERIMENT 1.2 2 P/P ∞ 1 P/P ∞ 0.8 0 0.4 -1 -2 0 0 1 2 3 4 5 6 0 30 60 90 120 150 180 Body Length(caliber) φ (windward=0, leeward=180) Circumference pressure Surface pressure 19/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Boat-Tail Design Drag curves Mach contours, Sr=1.45, M=0.85 20/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Boat-Tail Design Mach contours, Sr=1.45, M=0.85 21/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Aerodynamics for Man-Portable SAM Aerodynamic Analysis of Flexible Body Roll Induced Device Aerodynamic Interference Asymmetric Fin with Thrust Plume Spike Flow Simulation (Drag Reduction) 22/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Spike Design Unsteady turbulent flow, M=1.2 23/45 Missile Aerodynamics Branch, Agency for Defense Development
3 rd International Symposium on Integrating CFD and Experiments in Aerodynamics Jet Impingement onto Flat Plate Motor Characteristics Test Motor Full-Scale • Chamber Pressure 1200 psia 1750 psia • Chamber Temperature 2950 K 2970K • Thrust 330 lbs 1500 lbs • Throat Diameter 12.0 mm 67.0 mm • Exit Diameter 32.6 mm 182.6 mm • PR 1.87 2.33 • Exit Mach 2.93 2.93 24/45 Missile Aerodynamics Branch, Agency for Defense Development
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