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Preliminary experimental investigation of flutter characteristics of M and W wings

Description: Report presenting the results of nine experimental flutter tests involving two flat-plate models and two rib and spar models of NACA 0012 airfoil sections in order to give a comparison of the flutter characteristics of wings with M and W type plan forms. The W plan form generally gave higher flutter speeds than the M plan forms.
Date: August 8, 1951
Creator: Herr, Robert W.
Partner: UNT Libraries Government Documents Department

Derivation of the equations of motion of a symmetrical wing-tip-coupled airplane configuration with rotational freedom at the junctures

Description: From Summary: "The method of Lagrange multipliers is used to take account of the dynamic effects of the constraints at the wing tips when two identical airplanes are coupled to the wing tips of a "mother" airplane. The resulting equations of motion of this symmetrical configuration are derived for one, two, or three degrees of rotational freedom at each joint."
Date: October 8, 1951
Creator: Schy, Albert A.
Partner: UNT Libraries Government Documents Department

Damping in roll of rocket-powered test vehicles having swept, tapered wings of low aspect ratio

Description: From Summary: "Flight tests of rocket-powered models have been conducted to determine the damping in roll of a group of swept, tapered wings designed for flight in the transonic speed region. The Mach number range of these tests was from approximately 0.7 to 1.4. The experimental damping in roll for all configurations was less than predicted by linearized theory throughout the Mach umber range of these tests. The only wing in this group that experienced an appreciable transonic lateral trim change was the one with a 7-percent-thick circular-arc airfoil section."
Date: October 8, 1951
Creator: Sanders, E. Claude, Jr. & Edmondson, James L.
Partner: UNT Libraries Government Documents Department

Comparison of airfoil sections on two triangular-wing-fuselage configurations at transonic speeds from tests by the NACA wing-flow method

Description: Report presenting tests using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of four triangular-wing-fuselage models. Measurements of the normal force, chord force, and pitching moment for various angles of attack. Two models had wings of aspect ratio 2.31, one with an NACA 65-009 airfoil section and one with a 9-percent-thick biconvex section, and two with wings of aspect ratio 4, one with an NACA 65-006 airfoil and one with a 6-percent-thick double-wedge airfoil.
Date: August 8, 1951
Creator: Hall, Albert W. & McKay, James M.
Partner: UNT Libraries Government Documents Department

Flying qualities of a high-performance personal-owner airplane

Description: Report presenting an investigation to measure the flying qualities of a high-performance personal-owner airplane to investigate the possible causes of instrument flying accidents with that type of aircraft. Testing indicated that the lack of aerodynamic stall warning and rapid roll-off at the stall could contribute to stall-spin accidents with high-performance personal-owner aircraft. Results regarding the handling qualities and the control under instrument flying conditions are provided.
Date: November 8, 1951
Creator: Adams, James J. & Whitten, James B.
Partner: UNT Libraries Government Documents Department

Coolant-Flow Calibrations of Three Simulated Porous Gas-Turbine Blades

Description: An investigation was conducted at the NACA Lewis laboratory to determine whether simulated porous gas-turbine blades fabricated by the Eaton Manufacturing Company of Cleveland, Ohio would be satisfactory with respect to coolant flow for application in gas-turbine engines. These blades simulated porous turbine blades by forcing the cooling air onto the blade surface through a large number of chordwise openings or slits between laminations of sheet metal or wire. This type of surface has a finite number of openings, whereas a porous surface has an almost infinite number of smaller openings for the coolant flow. The investigation showed that a blade made of sheet-metal laminations stacked on a support member that passed up through the coolant passage was completely unsatisfactory because of extremely poor coolant flow distribution over the blade surface. The flow distribution for two wire-wound blades was more uniform, but the pressure drop between the coolant supply pressure and the local pressure on the outside of the blades was too low by a factor ranging from 3 to 3.5 for the required coolant flow rates. The pressure drop could be increased by forcing the wires closer together during blade fabrication.
Date: March 8, 1951
Creator: Esger, Jack B. & Lea, Alfred L.
Partner: UNT Libraries Government Documents Department

Longitudinal-control effectiveness and downwash characteristics at a Mach number of 1.24 of a 1/30-scale semispan model of the Bell X-5 airplane as determined by the NACA wing-flow method

Description: Report presenting an investigation at a Mach number of 1.24 using the NACA wing-flow method to determine the longitudinal-control effectiveness and downwash characteristics of a scale semispan model of the variable-sweep Bell X-5 airplane with the wind swept back at several different degrees. Lift, drag, and pitching moments were obtained for various angles of attack for several horizontal tail settings and with the tail off for each angle of sweep of the wing.
Date: January 8, 1951
Creator: Sawyer, Richard H.; Kennedy, Robert M. & Morris, Garland J.
Partner: UNT Libraries Government Documents Department

Estimated deceleration of airplane nose section jettisoned at various altitudes and airspeeds

Description: Memorandum presenting calculations made to determine the deceleration at any time after jettisoning of an airplane nose-section design typical of those which have been proposed as escape devices for high-speed airplanes. The decelerations were determined by two methods, one using successive approximations requiring graphical integration and the other giving reasonably close approximations by direct computation.
Date: January 8, 1951
Creator: Scher, Stanley H.
Partner: UNT Libraries Government Documents Department

Free-flight measurements at Mach numbers from 0.7 to 1.6 of some effects of airfoil-thickness distribution and trailing-edge angle on aileron rolling effectiveness and drag for wings with 0 and 45 degrees sweepback

Description: Report presenting the wing-aileron rolling effectiveness and drag for full-span sealed ailerons on untapered wings over a range of Mach numbers by using rocket-propelled test vehicles in free flight.
Date: October 8, 1951
Creator: Fields, E. M. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with 3-percent-thick, biconvex section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick, biconvex sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: June 8, 1951
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Some effects of fuselage interference, wing interference, and sweepback on the damping in roll of untapered wings as determined by techniques employing rocket-propelled vehicles

Description: Report presenting an experimental investigation utilizing rocket propelled vehicles in free flight to determine some effects of fuselage interference, wing interference, and sweepback on the damping-in-roll characteristics of untapered wings with an aspect ratio of 3.7 and NACA 65A009 airfoil sections between a range of Mach numbers.
Date: October 8, 1951
Creator: Bland, William M., Jr. & Dietz, Albert E.
Partner: UNT Libraries Government Documents Department

Sound from a two-blade propeller at supersonic tip speeds

Description: Report presenting sound measurements at static conditions for a two-blade, 47-inch-diameter propeller over a range of tip Mach numbers. For comparison, spectrums have been obtained at both subsonic and supersonic tip speeds. Results regarding the experimental results and comparison with theory are provided.
Date: May 8, 1951
Creator: Hubbard, Harvey H. & Lassiter, Leslie W.
Partner: UNT Libraries Government Documents Department

The Preparation, Physical Properties, and Heats of Combustion of Four Alkylsilanes

Description: Memorandum presenting a group of alkylsilanes consisting of monoethylsilane, diethylsilane, and trimethylsilane prepared in 65- and 90-percent yield by reduction of the respective alkylchlorosilanes with either lithium hydride or lithium aluminum hydride. The boiling points, densities, refractive indices, and freezing points were determined and presented with a survey of literature values.
Date: March 8, 1951
Creator: Tannenbaum, Stanley & Murphy, Maurice F.
Partner: UNT Libraries Government Documents Department