Question

Velocity profiles at upstream and downstream ends of a control volume shown below are measured as $u_1 = U_\infty$ and $u_2 = U_\infty \left(1 - (0.56)cos\left(\frac{\pi y}{2H_D}\right)\right)$ respectively. The height of the control volume at downstream, $H_D$ is equal to 0.022*c, where c is the chord length of the airfoil placed in the control volume. It is known that the flow is incompressible, two dimensional, and steady. The surfaces 3 and 4 are streamlines of the flow around the airfoil. The pressure, $P_\infty$ is constant over the entire surface of the control volume. Using the integral form of the continuity and momentum equation, calculate a) the height of the upstream station, $2H_U$ and b) the drag coefficient of the airfoil.

          Velocity profiles at upstream and downstream ends of a control volume shown below are measured as $u_1 = U_\infty$ and $u_2 = U_\infty \left(1 - (0.56)cos\left(\frac{\pi y}{2H_D}\right)\right)$ respectively. The height of the control volume at downstream, $H_D$ is equal to 0.022*c, where c is the chord length of the airfoil placed in the control volume. It is known that the flow is incompressible, two dimensional, and steady. The surfaces 3 and 4 are streamlines of the flow around the airfoil. The pressure, $P_\infty$ is constant over the entire surface of the control volume. Using the integral form of the continuity and momentum equation, calculate a) the height of the upstream station, $2H_U$ and b) the drag coefficient of the airfoil.

Velocity profiles at upstream and downstream ends of a control volume shown below are measured as u1 = U∞ and u2 = U∞(1 - (0.56)cos((π y)/(2HD))) respectively. The height of the control volume at downstream, HD is equal to 0.022*c, where c is the chord length of the airfoil placed in the control volume. It is known that the flow is incompressible, two dimensional, and steady. The surfaces 3 and 4 are streamlines of the flow around the airfoil. The pressure, P∞ is constant over the entire surface of the control volume. Using the integral form of the continuity and momentum equation, calculate a) the height of the upstream station, 2HU and b) the drag coefficient of the airfoil.

Added by Emilia U.

Question

Please give Ace some feedback