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Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Effects of split flaps, elevons, and leading-edge devices at low speed
Report presenting an investigation to evaluate the effects of split flaps, elevons, sharp leading edges, drooped-nose flaps, and extended-nose flaps on the lift, drag, and pitching-moment characteristics at low speed of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and an aspect ratio of 3.5. Results regarding the plain wing and wing-fuselage combinations, Reynolds number, split flaps, elevons, leading-edge devices, and highest lift coefficient attained before longitudinal instability are provided.
Date:
May 19, 1949
Creator:
Hopkins, Edward J.
System:
The UNT Digital Library
Analysis of measured pressures on airfoils at Mach numbers near 1
Report presenting measured pressure over airfoils at Mach number 1, with subsonic velocities at the nose and supersonic velocities throughout the rear portion, are analyzed by comparison with calculations for similar cases. Results regarding the theoretical basis of approximation, comparison of Prandtl-Meyer flow with measurements, comparison of linear-velocity extrapolation with measurements, and effect of boundary layer upon airfoil pressures are provided.
Date:
September 19, 1949
Creator:
Habel, Louis W. & Miller, Mason F.
System:
The UNT Digital Library
Chordwise and Spanwise Loadings Measured at Low Speed on Large Triangular Wings
Report presenting pressure distributions of three triangular wing models: a wing-alone model, the same wing combined with a body, and a mock-up of a triangular-wing airplane. Results regarding the separation-vortex air flow over triangular wings, general comments regarding the applicability of the study, chordwise pressure distribution, section lift characteristics, center of pressure, and span load distribution are provided.
Date:
April 19, 1949
Creator:
Anderson, Adrien E.
System:
The UNT Digital Library
Cyclic engine operation of cast vitallium turbine blades at an exhaust-cone gas temperature of 1440 plus or minus 20 F
Report presenting an investigation conducted to determine the effects of increased gas temperatures on the performance of cast Vitallium blades in a turbojet engine. Results regarding the experimental investigation and metallurgical investigation are provided.
Date:
September 19, 1949
Creator:
Yaker, Charles & Garrett, Floyd B.
System:
The UNT Digital Library
Investigation of Low-Speed Aileron Control Characteristics at a Reynolds Number of 6,800,000 of a Wing With Leading Edge Swept Back 42 Degrees With and Without High-Lift Devices
Report presenting an investigation at a Reynolds number of 6,800,000 to determine the low-speed lateral control characteristics of a 20-percent-chord half-span outboard aileron on a wing with 42 degrees of sweepback at the leading edge. The lateral control, aileron hinge-moment, aileron load, and balance-chamber-pressure characteristics were determined for the wing with and without high-lift and stall-control devices for an angle-of-attack range from -4 degrees through the stall.
Date:
July 19, 1949
Creator:
Bollech, Thomas V. & Pratt, George L.
System:
The UNT Digital Library
Two-Dimensional Wind-Tunnel Investigation of Two NACA 6-Series Airfoils With Leading-Edge Slats
Report presenting an investigation of two NACA 6-series airfoils, the NACA 64(sub)1-212 and NACA 65A109 with leading edge slats and split flaps deflected 60 degrees. Information about optimum slat positions, airfoil section lift characteristics, pitching-moment characteristics, and effect of roughness on the lift characteristics was obtained.
Date:
January 19, 1949
Creator:
Gottlieb, Stanley M.
System:
The UNT Digital Library