I am trying to determine the lift and drag coefficients for a 2-D flat plat ( 0.1 m chord x 0.0166667 m height ) oriented perpendicular to an air flow with Re of 10^4 using the Spallart-Almaras Turbulent Flow module. My primary concern is in matching the "textbook value" for C_d -- My COMSOL run returns 2.00615 whereas I'm expecting the value to be around 0.9.
I am following the method described in the Flow Past a Cylinder Tutorial. I am evaluating the drag force over the boundary integral of my flat plate. I then compute C_d = - 2*reacf(u)/(spf.rho*V^2*height).
Can someone tell me where I might be going wrong? I have attached my COMSOL model for your reference.
v/r
Connor
I am following the method described in the Flow Past a Cylinder Tutorial. I am evaluating the drag force over the boundary integral of my flat plate. I then compute C_d = - 2*reacf(u)/(spf.rho*V^2*height).
Can someone tell me where I might be going wrong? I have attached my COMSOL model for your reference.
v/r
Connor