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Lateral-Control Investigation at a Reynolds Number of 5,300,000 of a Wing of Aspect Ratio 5.8 Sweptforward 32 Degrees at the Leading Edge
Memorandum presenting the low-speed lateral control characteristics of a 32 degree sweptforward wing of aspect ratio 5.8 and NACA 65-series airfoil sections as determined in the 19-foot pressure tunnel. The investigation include the measurement of the hinge-moment and normal-force characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and several configurations of spoilers.
Date:
February 7, 1950
Creator:
Graham, Robert R.
System:
The UNT Digital Library
Low-speed static longitudinal stability and control characteristics of 60 degree triangular-wing and modified 60 degree triangular-wing models having half-delta and half-diamond tip controls
Report presenting a low-speed investigation in the stability tunnel to determine the static longitudinal stability and control characteristics of two wing-fuselage combinations equipped with wing-tip controls of half-diamond and half-delta plan form. Results regarding the effect of control area and plan form on control characteristics and on trim characteristics are provided.
Date:
February 7, 1952
Creator:
Lichtenstein, Jacob H. & Jaquet, Byron M.
System:
The UNT Digital Library
Free-spinning-tunnel investigation to determine the effect of spin-recovery rockets and thrust simulation on the recovery characteristics of a 1/25-scale model of the Chance Vought XF8U-1 airplane: TED No. NACA DE 392
Report presenting an investigation of a model of the Chance Vought XF8U-1 airplane to determine the effect of spin-recovery rockets on the recovery characteristics of the model. The investigation also included tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. Results regarding yaw rockets, thrust-simulation rocket, and roll rockets are provided.
Date:
February 7, 1955
Creator:
Burk, Sanger M., Jr. & Lee, Henry A.
System:
The UNT Digital Library
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102B Airplane at Mach Numbers of 1.41, 1.61, and 2.01: Coord No. AF-231
Report discussing testing of a scale model of the Convair F-102B to determine its aerodynamic characteristics at several Mach numbers. Four basic body modifications and two afterbody configurations were evaluated.The body modifications were all found to slightly reduce values of minimum drag, but did not cause a change in the static stability and lift-curve-slope values compared to the F-102A.
Date:
February 7, 1956
Creator:
Driver, Cornelius & Robinson, Ross B.
System:
The UNT Digital Library
Lift, drag, and static longitudinal stability characteristics of configurations consisting of three triangular wing panels and a body of equal length at Mach numbers from 3.00 to 6.28
Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for three highly swept three-wing tailless configurations determined from tests at a range of Mach numbers and angles of attack.
Date:
February 7, 1956
Creator:
Savin, Raymond C. & Wong, Thomas J.
System:
The UNT Digital Library
A study of a missile designed to fly at low speed with its longitudinal axis aligned with the flight path
An experimental investigation to explore the practicability of a low-speed missile designed to fly with its longitudinal axis pointing along the flight path. The wing and tail surfaces were arranged in a cruciform pattern and the incidence was selected to trim the missile at the desired normal-force coefficient with the body at 0 degrees angle of attack. Results regarding the description of a self-balancing missile and experimental results are provided.
Date:
February 7, 1956
Creator:
Hopkins, Edward J. & Sorensen, Norman E.
System:
The UNT Digital Library