Theoretical Investigations, and Correlative Studies for NLF, HLFC, and LFC Swept Wings at Subsonic, Transonic and Supersonic Speeds

The results of theory/experiment correlative studies at subsonic and supersonic Mach numbers are presented in this paper. These studies were conducted by using theoretical design tools consisting of the Method of Characteristics, newly-developed integral compressible boundary-layer methods for infinitely swept wings, namely, laminar boundary layer with suction, prediction of neutral instability and transition due to amplification of Tollmien-Schlichting (T.S.) waves and crossflow (C.F.), and a method for predicting separating turbulent boundary-layer characteristics. Results of correlations have indicated that the present integral boundary layer methods are quite successful in predicting transition phenomenon both at transonic and supersonic speeds. Correlations performed at subsonic and transonic Mach numbers have indicated that results of computations by the present methods for wings with sweep angles in the range of 0° to 50°, Reynolds number range of 1 to 30 million, and with and without boundary-layer suction, are in good agreement with experimental data. For supersonic freestream conditions correlative studies have been performed by the present methods for flat plate, biconvex airfoils, and bodies of revolution, and these results have also been found very encouraging.