The TNO model, a trailing edge noise prediction method, is validated, modified, and analyzed for various input formats. Two different methods are used to calculate the flow field for this model: Reynolds averaged Navier-Stokes (RANS) and a viscous panel method, XFOIL. It is found that the RANS-based TNO model show good agreement with the experiments but the XFOIL-based TNO was found to overpredict the turbulence kinetic energy and, consequently, the sound pressure level. A modification is made in the XFOIL-based TNO model by substituting Prandtl's mixing length hypothesis from the original model with a new blended model consisting of the mixing length hypothesis and the Cebeci-Smith eddy viscosity model. Twenty-six different test cases are tested with airfoils: NACA 0012, NACA 0015, NACA 64-618, NACA 643-418, and DU 96-w-180. RANS input to the TNO model is able to predict the sound pressure spectrum to within 3 dB for the frequency range of 800Hz to 2000Hz in 16 of the 26 cases. The new blended model is found to show clear improvements to the prediction for 14 out of the 26 cases when compared to the original XFOIL input. Moreover, the new XFOIL input was able to predict sound pressure level to within 3 dB for 14 of the 26 cases. Overall, the new proposed model improves the prediction for the XFOIL-based TNO model.
|Commitee:||Robinson, Stephen, Sarigul-Klijn, Nesrin|
|School:||University of California, Davis|
|Department:||Mechanical and Aerospace Engineering|
|School Location:||United States -- California|
|Source:||MAI 58/02M(E), Masters Abstracts International|
|Subjects:||Engineering, Aerospace engineering|
|Keywords:||TNO model, Trailing edge noise|
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