MAE 352: Experimental Aerodynamics II
MAE 352 introduces juniors to the supersonic wind tunnel. Students learn about flow visualization using surface streaklines, shock visualization using Schlieren photography, pressure measurement using pressure-sensitive paint, and flow through nozzles. Students are introduced to advanced data processing techniques such as image processing.
Experiments
- Wind Tunnel Block Calibration: Calibrate the block number setting for the wind tunnel against the speed obtained in the test section using a pitot tube and the isentropic and Rayleigh equations for supersonic flows.
( Handout | Powerpoint ) - Shock Wave Analysis: The oblique shock wave in front of a wedge in a supersonic flow is captured using Schlieren photography. The angle of the shock is obtained by image processing using edge detection algorithms. The speed of the flow can then be deduced from the angle of the shock using the $latex \theta$-$latex \beta$-$latex M$ equation.
( Handout | Powerpoint ) - Surface Flow Visualization: The flow on the surfaces of various shapes is examined using dye flow visualization. The surface is coated in a dye-mineral oil mixture that flows with the wind and indicates flow features on the surface such as boundary layer separation, shocks, and tip vortices.
( Powerpoint ) - Nozzle Analysis: Flow through converging and converging-diverging nozzles is analyzed. Using pressure and temperature probes inserted at regular intervals along the length of the nozzle, various regimes of flow such as subsonic flow, choked flow, underexpanded flow and overexpanded flow are studied.
( Handout 1 2 | Powerpoint 1 2 ) - Pressure-Sensitive Paint: The pressures on the surface of a wedge are analyzed using PSP.
( Handout | Powerpoint )
