Wind-tunnel buffeting measurements on two wing end-plate airplane model configurations

During the course of wind-tunnel force tests on a 1/30-scale model of a proposed subsonic nuclear -powered airplane in the Langley 16 -foot transonic tunnel, wing-buffeting measurements were made on two different wingend-plate model configurations.The low-aspect-ratio (3.6) wing had a leading-edge sweepback angle of 51°, and the highaspect-ratio (6.0) wing had a leading-edge sweepback angle of 36O.The model support system introduced undesirable buffeting response vibration modes in the same frequency range as the model wing vibration modes.On a comparative basis, the high-aspect-ratio wing configuration generally exhibited a more abrupt entry into buffeting with increasing angle of attack and had a lower lift coefficient for the onset of buffeting than that of the lowasp ec t -r atio wing configuration.