NACA-RM-L52K19

Abstract

INTRODUCTON <br>The bulk of available design data for supersonic aircraft and missiles lies. in the speed range up to a Mach number of roughly 2. A considerable increase has recently occurred in contemplated design speeds, and thus the need for research data in the speed range from Mach number 2 to about 5 has greatly increased. In order to provide some of the needed data,a wing program has been started in the Langley 9- by 9-inch Mach number 4 blow-down jet. This program has two objectives: first, to establish the performance at Mach number 4.04 of a number of related wings of particular interest in this speed ranges and second, to develop if possible means of correlation with the available results for other supersonic Mach numbers. In this program the effects of plan form thickness ratio, maximum-thickness location, and leading-and trailing edge profiles on wing force characteristics are being investigated. <br>This report presents the results obtained for two8-percent-thick wings of this program which differed only in the position of maximum thickness. One of these wings was identical to a wing previously investigated at Mach numbers of 1.62, 1.92, and2.40in the Langley 9-inch supersonic tunnel (ref.1). Also presented for comparison are recently obtained preliminary results for these and similar wings from the Langley 9-inch supersonic tunnel and from the Langley 11-inch hypersonic tunnel ( Mach number 6.9). These new data, together with the published results in references 1 and 2, are analyzed and discussed briefly with a view toward establishing correlation criteria