Prediction of Airfoil Tone Frequencies

techniques QN x 10~ -9.3, 10.5, 20.9, for CSORb, GSb, and Jb, respectively and QNA0 >9.3 for SO/?/, due to computational times incurred in determining the optimum value of a( = 1.1 in this case). Testing of the four techniques for other configurations and Mach numbers, subsonic and supersonic, have been performed within the methods of Ref. 1 with essentially equivalent results. Thus, it has been demonstrated that the use of CSOR b results in material savings in computational times over the use of Jh, GSh, andSORh.