Analysis and Design of a Cooled Supercritical Airfoil Test Model.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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A wind tunnel test model of a supercritical airfoils was designed to investigate the wall cooling effect on subsonic boundary layer stability. A DSMA 523 airfoil section was employed. The model was designed to have surface temperature instrumentation and a liquid nitrogen cooling system. Heat transfer, aerodynamic loads and stresses, and instrumentation were analyzed for the proposed test conditions. A computer program was developed to analyze the forced, convective heat transfer over a two-dimensional body with a constant wall temperature. The program utilized an integral method to compute local Santon numbers. Local heat flux and total heat flow were predicted for a Mach number of 0.7, Reynolds numbers of 0.923 x 10 to the 6th power and 1.673 x 10 to the 6th power, and cooling ratios from 1.000 to 0.824. The stress analysis consisted of applying beam bending theory, along with some simplifying assumptions, to the model. Construction drawings and specified test conditions for Mach numbers of 0.3, 0.5, and 0.7 are included. The proposed test are to be conducted in the subsonic test section of the Trisonic Test Facility at Wright-Patterson AFB, Ohio. Author
- Fluid Mechanics