THE SUBSONIC STATIC AERODYNAMIC CHARACTERISTICS OF AN AIRPLANE MODEL HAVING A TRIANGULAR WING OF ASPECT RATIO 3Ⅰ - EFFECTS OF HORIZONTAL-TAIL LOCATION AND SIZE ON THE LONGITUDINAL CHARACTERISTICS

摘要

An investigation has been conducted to determine the effects of horizontal-tail location and size on the longitudinal aerodynamic characteristics of an airplane model having a triangular wing. The wing had an aspect ratio of 3 and the NACA 0003.5-63 section in the streamwise direction. Two horizontal tails were tested which had areas of either I6.7 or 21.9 percent of the wing area. Each of the horizontal tails had an aspect ratio of 4, a taper ratio of 0.33, the NACA 0004-64 section, and no sweepback of the 50-percent-chord line. Tests were conducted with the horizontal tails located -0.10, 0, 0.10, and 0.20 wing semispan above the chord plane of the wing at longitudinal distances of 1.2 and 1.5 mean aerodynamic chord lengths behind the moment center. The wind-tunnel tests were conducted at a Reynolds number of 2.5 million at Mach numbers from 0.25 to 0.95.