Accession Number:

AD0270497

Title:

WIND TUNNEL TESTS OF AN UNMANNED FOLDING DELTA-WING HYPERSONIC GLIDER. PART II. LATERAL STATIC STABILITY AND CONTROL AT MACH NUMBERS OF 0.80, 1.86, AND 2.87

Descriptive Note:

Corporate Author:

DAVID TAYLOR MODEL BASIN WASHINGTON DC

Personal Author(s):

Report Date:

1961-12-01

Pagination or Media Count:

78.0

Abstract:

Tests were performed in the 18- by 18-inch supersonic wind tunnel on a 0.042-scale model of an unmanned, delta-wing hypersonic glider at Mach numbers of 0.80, 1.86, and 2.87. During this phase of testing the lateral characteristics were determined for both folded and unfolded configurations. The effectiveness of various locations and deflections of wing and body spoilers as a means of lateral control was determined. There was a wide variation in the effectiveness of this type of controller. Degree and direction of control varied with location, deflection, and Mach number. Two different sizes of vertical fins were tested. The larger fin contributed greater directional stability but detracted from dihedral effect. The most consistent spoiler performance was obtained with the larger fin. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE