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Calculating moment of inertia of a NACA-0012 wing for pitching motion |
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March 28, 2020, 11:06 |
Calculating moment of inertia of a NACA-0012 wing for pitching motion
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Rohan Srikanth
Join Date: Mar 2020
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Hey, so I am trying to simulate the pitching motion of a NACA-0012 wing and I went through the tutorial. I used 6-DOF rigidbodyofmotion solver. I am unable to accurately determine the moment of inertia of the wing. Due to this, my angular velocity seems to blow up after a while.
Can anyone please help me with it? 13.6 gm wing with a chord length of 0.15m, span of 0.15m and the max thickness is 0.018m. I want it to pitch (not plunge) from 0 to 18 degrees at 0.0314 rad/s. I have added my dynamicMeshDict file for reference. dynamicFvMesh dynamicMotionSolverFvMesh; motionSolverLibs ("libsixDoFRigidBodyMotion.so"); solver sixDoFRigidBodyMotion; sixDoFRigidBodyMotionCoeffs { patches (airfoil); innerDistance 0.15; outerDistance 0.3; mass 0.0136; centreOfMass (0.06024 0 0); momentOfInertia (1.462e-4 0.892e-4 0.593e-2); orientation ( 1 0 0 0 1 0 0 0 1 ); angularMomentum (0 1.96202e-05 0); g (0 0 -9.81); rho rhoInf; rhoInf 1; report on; solver { type symplectic; } constraints { zLine { sixDoFRigidBodyMotionConstraint point; centreOfRotation (0.0375 0 0); direction (0 0 1); } yAxis { sixDoFRigidBodyMotionConstraint axis; axis (0 1 0); } } } restraints { verticalSpring { sixDoFRigidBodyMotionRestraint linearSpring; anchor (0.0375 0 0); // 1 or 0? refAttachmentPt (0.0375 0 0); stiffness 4000; damping 2; restLength 0; } axialSpring { sixDoFRigidBodyMotionRestraint linearAxialAngularSpring; axis (0 1 0); stiffness 700; damping 0.5; } // ************************************************** *********************** // |
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dynamicmeshdict, naca-0012, pimpledymfoam, pitching, wingmotion |
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