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Wind-Tunnel Tests of a 0.16-Scale Model of the Douglas MX-656 Airplane at High Subsonic Speeds, 1, Stability and Control Characteristics

Description: Wind tunnel tests of the 0.16-scale Douglas MX-656 model were made at low and high subsonic Mach numbers to investigate the static longitudinal- and lateral stability characteristics. The tests shows that undesirable changes in longitudinal stability at the stall were apparently caused by an altered downwash pattern at the tail. The jettisonable nose fins were highly destabilizing. Compressibility effects for the test Mach numbers were not detrimental to the longitudinal- or lateral-stability characteristics.
Date: April 26, 1949
Creator: Hamilton, William T. & Cleary, Joseph W.
Partner: UNT Libraries Government Documents Department

Correlation of the drag characteristics of a typical pursuit airplane obtained from high-speed wind-tunnel and flight tests

Description: In order to obtain a correlation of drag data from wind-tunnel and flight tests at high Mach numbers, a typical pursuit airplane, with the propeller removed, was tested in flight at Mach numbers up to 0.755, and the results were compared with wind-tunnel tests of a 1/3-scale model of the airplane. The tests results show that the drag characteristics of the test airplane can be predicted with satisfactory accuracy from tests in the Ames 16-foot high-speed wind tunnel of the Ames Aeronautical Laboratory at both high and low Mach numbers. It is considered that this result is not unique with the airplane.
Date: January 1, 1948
Creator: Nissen, James M; Gadebero, Burnett L & Hamilton, William T
Partner: UNT Libraries Government Documents Department

Summary report on the high-speed characteristics of six model wings having NACA 65(sub1)-series sections

Description: A summary of the results of wind-tunnel tests to determine the high-speed aerodynamic characteristics of six model wings having NACA 65sub1-series sections is presented in this report. The 8-percent-thick wings were superior to the 10-percent and 12-percent-thick wings from the standpoint of power economy during level flight for Mach numbers above 0.76. However, airplanes that are to fly at Mach numbers below 0.76 will gain aerodynamically if the percentage thickness of the wing and the aspect ratio are both increased. The lift-curve slopes for the 8-percent-thick wings at 0.85 Mach number were roughly twice their low-speed values.
Date: October 19, 1945
Creator: Hamilton, William T. & Nelson, Warren H.
Partner: UNT Libraries Government Documents Department

Doctoral Programs in Mathematics and Education as Related to Instructional Needs of Junior Colleges and Four Year Colleges

Description: The problem of this study was to analyze doctoral programs in mathematics and education for the preparation of teachers of undergraduate mathematics. The purpose of the study was to determine (1) the need for such programs, (2) the attitude of college and university officials toward them, (3) the composition of present offerings and (4) recommendations to the future course their development should take.
Date: June 1967
Creator: Hamilton, William Wingo
Partner: UNT Libraries

Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: stability and control characteristics

Description: Report presenting static lateral- and longitudinal-stability tests of a scale model of a projected, low-aspect-ratio, supersonic airplane at low and high subsonic Mach numbers. The wing was equipped with leading-edge flaps and had a modified double-wedge airfoil with sharp leading and trailing edges. Results regarding lift characteristics, static longitudinal stability and control, lateral and directional stability, drag characteristics, and wing and fuselage tuft studies are provided.
Date: April 21, 1950
Creator: Hamilton, William T. & Cleary, Joseph W.
Partner: UNT Libraries Government Documents Department