Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon (open access)

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon

Report presenting a wind-tunnel investigation of a semispan model of a wing swept back 63 degrees with an aspect ratio of 3.5 and a taper ratio of 0.25. The tests were conducted to evaluate the effects of Reynolds and Mach number on the aerodynamic characteristics of the wing. Results regarding the characteristics of the wing with the elevon undeflected, effectiveness of the elevon, effects of roughness strips, and effect of model deflection under varying loads are provided.
Date: October 11, 1948
Creator: Reynolds, Robert M. & Smith, Donald W.
System: The UNT Digital Library
Comparison of Hovering Performance of Helicopters Powered by Jet-Propulsion and Reciprocating Engines (open access)

Comparison of Hovering Performance of Helicopters Powered by Jet-Propulsion and Reciprocating Engines

Report presenting an investigation of the maximum hovering time, or the time that a helicopter can sustain itself without motion, for helicopters using a reciprocating engine, by ramjet engines at the tips of rotor blades, and by pulse-jet engines at the tips of rotor blades. Testing showed that the reciprocating engine permitted much longer hovering time than the jet-propulsion engines, but the jet-propulsion engines were much lighter and could lift greater disposable loads.
Date: June 11, 1948
Creator: Brightwell, Virginia L.; Peters, Max D. & Sanders, J. C.
System: The UNT Digital Library
Flight Tests of a Two-Dimensional Wedge Diffuser at Transonic and Supersonic Speeds (open access)

Flight Tests of a Two-Dimensional Wedge Diffuser at Transonic and Supersonic Speeds

"A two-dimensional wedge diffuser, designed to be used with a ducted-airfoil ram jet, was tested on a rocket-powered test vehicle up to a Mach number of 1.45. Orifice plates and a choking section behind the diffuser exit simulated burning in a combustion chamber by providing the proper pressure drop. Results obtained from these tests showed there was no abrupt changes in mass flow and pressure recovery as the model velocity increased through the transonic region" (p. 1).
Date: August 11, 1948
Creator: Faget, M. A.
System: The UNT Digital Library
An Investigation of the Downwash Behind a High-Aspect-Ratio Wing With Various Amounts of Sweep in the Langley 8-Foot High-Speed Tunnel (open access)

An Investigation of the Downwash Behind a High-Aspect-Ratio Wing With Various Amounts of Sweep in the Langley 8-Foot High-Speed Tunnel

Report presenting measurements of downwash angles at points at two vertical positions at the probable tail location behind a high-aspect-ratio wing with an NACA 65-210 section with no sweep and 30 degrees and 45 degrees of sweepback and sweepforward in conjunction with a fuselage.
Date: May 11, 1948
Creator: Whitcomb, Richard T.
System: The UNT Digital Library
Safety Tests on Hand Stacking of U-235 Cubes (open access)

Safety Tests on Hand Stacking of U-235 Cubes

From abstract: "Critical assembly tests have been made on the Pajarito Universal Machine to determine the safety limits of handstacking cubes of 95% U-235 in spherical geometries preparatory to making critical assemblies of U-235 in an "infinite" tuballoy tamper. The U-235 cubes were stacked as pseudospheres in a cavity at the top of a tuballoy block 12" high and 8" on a side, and the assembly tamped by locating it inside a doughnut shaped water tank whose tamping effect is equivalent to the tamping caused by personnel necessary for hand stacking."
Date: October 11, 1948
Creator: Josephson, V.; Young, D. S. & Dike, R. S.
System: The UNT Digital Library