NACA-RM-A53A30

Abstract

INTRODUCTION <br>In selecting a wing for a high-speed interceptor airplane, the designer has the choice of a large variety of possible shapes. Since an intelligent selection requires a knowledge of the effects of the various shape parameters on the aerodynamic characteristics of the wings, a program to provide information was formulated at the Ames Laboratory in the latter part of 1950. The purpose of this program was twofold: <br>1. To investigate at Mach numbers from 0.25 to 1.9 the effects of type of plan form, aspect ratio, thickness, thickness distribution, and wing camber and twist for wing-body combinations. Such combinations would be selected to minimize the effects of other differences generally present An a comparison of data obtained from several facilities, such as body shape, body size, and Reynolds number. <br>2. To provide data at supersonic speeds to fill the gap existing between tests made at low Reynolds number over a range of angle of attack in small wind tunnels and tests with rocket-powered models made at high Reynolds number, but generally at zero lift. <br>When the program at the Ames Laboratory was first formulated, it was realized that a considerable period of time would elapse before its completion because of the time required to construct and test the models. Furthermore, it was desired to maintain a certain amount of fluidity in the program so that parts might be added to the program as it progressed. Because of the time involved, it was decided to expedite publication of the results by reporting the data obtained for each wing-body combination immediately after testing. These reports (refs. I to 17) were brief and no analysis of the data was attempted. The purpose of the present report is therefore to compare and to analyze these data. The data will also be used to ascertain the adequacy of existing theoretical solutions in predicting the lift_ drag_ and pitching-moment characteristics of low-aspect ratio wing and body combinations. <br>The large amount of data obtained during this program prevents a presentation in graphical form of all the results. However_ for the interested reader_ all the data are presented in tables I through XIX.