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Free-spinning-tunnel tests of a 1/23.75-scale model of the Douglas DC-3 airplane

Description: Report presenting testing of a model of the Douglas DC-3 airplane for several loading conditions. The load factor for the complete airplane, for the horizontal tail, and the force to start moving the elevator downward were estimated for some steady spins. Testing occurred at 2500 feet and 10,000 feet.
Date: June 1942
Creator: MacDougall, George F., Jr.
Partner: UNT Libraries Government Documents Department

Wind Tunnel Investigation of the Effects of Slot Shape and Flap Location on the Characteristics of a Low-Drag Airfoil Equipped with a 0.25-Chord Slotted Flap

Description: Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag.
Date: December 1944
Creator: Holtzclaw, Ralph W. & Weisman, Yale
Partner: UNT Libraries Government Documents Department

Tests of two models representing intermediate inboard and outboard wing sections of the XB-36 airplane

Description: Report presenting testing in the two-dimensional low-turbulence pressure tunnel and the two-dimensional low-turbulence tunnel of two models made by the Consolidated Aircraft Corporation, one of the outboard section and one of the inboard section.
Date: January 1943
Creator: Bogdonoff, Seymour M.
Partner: UNT Libraries Government Documents Department

Loss of xylidines in overwater storage of xylidine-blended fuel

Description: Tests were undertaken to determine the relationships for estimating the maximum amount of a water-soluble gasoline additive that will diffuse from the gasoline to the water when fuel is stored over the water and to determine from the relationships the amount of xylidines that will diffuse from the gasoline to the water in an overwater-storage system.
Date: March 1944
Creator: Tischler, Adelbert O. & Tischler, Adelbert O.
Partner: UNT Libraries Government Documents Department

Investigation of Diving Moments of a Pursuit Airplane in the Ames 16-Foot High Speed Wind Tunnel

Description: From Summary: "A pursuit type airplane encountered severe diving moments in high-speed dives which make recovery difficult. For the purpose of investigating these diving moments and finding means for their reduction, a 1/6 scale model of the airplane was tested in the 16-foot high-speed wind tunnel at Ames Aeronautical Laboratory. The test results indicate that up to a Mach number of at least 0.75, the limit of the tests, the dive-recovery difficulties can be alleviated and the longitudinal maneuverability improved by the substitution of a long symmetrical fuselage for the standard fuselage."
Date: October 1942
Creator: Erickson, Albert L.
Partner: UNT Libraries Government Documents Department

Measurements of flying qualities of a Curtiss SB2C-1 airplane (number 00014)

Description: Report presenting an investigation of the flying qualities of a Curtiss SB2C-1 airplane. Tests were made to determine the effect of a bobweight in the elevator system and the effect of seals in the aileron gaps. Results regarding longitudinal stability and control, requirements for lateral stability and control, and stalling characteristics are provided.
Date: March 1944
Creator: Phillips, W. H.; Williams, W. C. & Hoover, H. H.
Partner: UNT Libraries Government Documents Department

Flight tests of beveled-trailing-edge ailerons with various modifications on a North American XP-51 airplane (AAF No.41-38)

Description: Report presenting flight testing using a North American XP-51 airplane with several arrangements of beveled-trailing-edge ailerons to determine the most satisfactory arrangement. Results regarding the aileron configuration, trimming tabs, and factors affecting symmetry of aileron characteristics are provided.
Date: December 1943
Creator: White, Maurice D. & Hoover, Herbert H.
Partner: UNT Libraries Government Documents Department

Operating stresses in aircraft-engine crankshafts and connecting rods 2: instrumentation and test results

Description: Report presenting an investigation to develop methods and equipment for the measurement of operating stresses in aircraft-engine crankshafts and connecting rods. The results indicate that the measurement of stresses in connecting rods is feasible. Results regarding stresses in the crankshaft and stresses in the master connecting rod are provided.
Date: August 1945
Creator: Dutee, Francis J.; Phillips, Franklyn W. & Calvert, Howard F.
Partner: UNT Libraries Government Documents Department

Comparison of free-spinning wind-tunnel results with corresponding full-scale spin results

Description: Report presenting a study of comparable information on full-scale spinning results and NACA free-spinning wind-tunnel results in order to determine the degree of reliability of tunnel results in predicting the spinning behavior of airplanes. Satisfactory agreement between model and airplane was found in 16 instances and disagreement was found in 5 instances.
Date: December 1938
Creator: Seidman, Oscar & Neihouse, A. I.
Partner: UNT Libraries Government Documents Department

Resistance Tests of a 1/16 Size Model of the Hughes-Kaiser Flying Boat, NACA Model 183

Description: Tank tests were made of a hull model of the Hughes-Kaiser cargo airplane for estimates of take-off performance and maximum gross load for take-off. At hump speeds, with the model free to trim, the trim and resistance were high, which resulted in a load-resistance ratio of approximately 4.0 for a gross load coefficient of 0.75. With a 4000,000-lb load, the full size craft may take off in 69 sec over a distance of 5600 ft.
Date: June 1944
Creator: Olson, Roland E.; Posner, Jack & Woodward, David R.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Tests of a Portion of a PV-2 Helicopter Rotor Blade

Description: From Summary: "A portion of a PV-2 helicopter rotor blade has been tested in the 6- by 6-foot test section of the Langley stability tunnel to determine if the aerodynamic characteristics were seriously affected by cross flow or fabric distortion. The outer portion of the blade was tested as a reflection plane model pivoted about the tunnel wall to obtain various angles of cross flow over the blade. Because the tunnel wall acts as a plane of symmetry, the measured aerodynamic characteristics correspond to those of an airfoil having various angles of sweepforward and sweepback. Tests were made with the vents on the lower surface open and also with the vents sealed and the internal pressure held at -20 inches of water producing an internal pressure coefficient of -1.059."
Date: March 29, 1945
Creator: Kemp, William B., Jr.
Partner: UNT Libraries Government Documents Department

Flight tests of various tail modifications on the Brewster XSBA-1 airplane 3: measurements of flying qualities with tail configuration 3

Description: Report presenting a series of tests on the Brewster XSBA-1 airplane to determine the effects of various tail modifications. Some of the modifications include variations of the chord of the elevator and rudder while the span and total area of the surfaces are kept constant and variations of the total area of the vertical tail surface. Results regarding the longitudinal stability and control and lateral stability and control are provided.
Date: July 1944
Creator: Crane, H. L. & Reeder, J. P.
Partner: UNT Libraries Government Documents Department

Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Description: Report presenting an investigation of three interchangeable sealed-gap 0.20-airfoil-chord plain ailerons of different contour on the NACA 65(sub 1)-210 airfoil section. The three aileron contours tested were the true airfoil contour, straight sides, and a beveled trailing edge. Results regarding the aileron effectiveness, aileron hinge moments, lift, pitching moment, and drag are provided.
Date: December 1945
Creator: Underwood, William J.; Braslow, Albert L. & Cahill, Jones F.
Partner: UNT Libraries Government Documents Department

Flight tests of a pursuit airplane fitted with an experimental bellows-type bob weight

Description: Report presenting flight tests to determine the longitudinal stability characteristics of a pursuit airplane when flown with and without an experimental bellows-type bob weight. When the weight was installed, the stick-free static stability remained approximately constant irrespective of the shift in center of gravity resulting from a change in fuel quantity in the auxiliary fuselage fuel tank. Although the weight functioned satisfactorily, the performance could have been enhanced by the reduction of the friction in the mechanism.
Date: October 1944
Creator: Spreiter, John R. & Nissen, James M.
Partner: UNT Libraries Government Documents Department

General free to trim tests in NACA tank no.2 of three 1/8-full-size models of flying-boat hulls at low speeds-NACA models 116E-3K, 120R, and 143

Description: Report presenting tests of representative models of flying boat hulls to determine the resistance at low speeds. Results regarding the effect of load coefficients, resistance coefficients, and towing and drifting calculations are provided.
Date: January 1943
Creator: Carter, Arthur W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of a section of the horizontal tail surface for the Bell XP-63 airplane

Description: Report presenting force tests conducted on a model of a section of the XP-63 horizontal tail surface in the 4- by 6-foot closed-throat vertical wing tunnel. The angle-of-attack range was from the negative to the positive stall for all flap deflections.
Date: August 1941
Creator: Ames, Milton B., Jr. & Hoggard, H. Page, Jr.
Partner: UNT Libraries Government Documents Department

The effect of xylidines on the load-carrying capacity of an aircraft-engine oil 1

Description: Report presenting testing to determine the effect of xylidines on the load-carrying capacity of aircraft-engine oil in several test devices. Lubricating oil and lubricating oil with xylidines added was tested in four different testing machines. In all of the experiments, adding the xylidines made the oil a poorer lubricant in the boundary region of lubrication, where metal-to-metal contact occurs.
Date: August 1943
Creator: Spurr, Robert A. & Olson, Walter T.
Partner: UNT Libraries Government Documents Department

The effect of xylidines on the corrosiveness of aircraft-engine oil

Description: Report presenting testing to determine the effect of xylidines of the corrosiveness of aircraft-engine oil toward engine bearings as part of an investigation on the suitability of xylidines as an antiknock component in aviation gasoline. Results regarding the loss in bearing weight, corrosion losses, temperature characteristics, and types of corrosion are provided.
Date: July 1943
Creator: Meyrowitz, Emanuel & Olson, Walter T.
Partner: UNT Libraries Government Documents Department

Gasoline-water distribution coefficients of xylidines

Description: Report presenting experimental data on the distribution coefficients of technical xylidines for the system gasoline-water. The distribution coefficient is defined as the ratio of the concentration of xylidines in the gasoline layer to that in the water layer. Results regarding the effect of concentration of xylidines, effect of aromatic content of fuel, effect of sea water, and effect of temperature are provided.
Date: June 1943
Creator: Tischler, Adelbert O.; Slabey, Vernon A. & Olson, Walter T.
Partner: UNT Libraries Government Documents Department

The low-temperature solubility of technical xylidine in aviation gasoline

Description: Report presenting testing to determine the low-temperature solubility of technical xylidines in aviation gasoline. Testing included measuring the cloud point, or incipient separation temperature, at several concentrations of technical xylidines in a 65-octane-number clear gasoline without aromatics and with aromatics added in various percentages up to 15 percent by volume and a grade 130, specification AN-F-28, amendment 2, gasoline.
Date: June 1943
Creator: Olson, Walter T.
Partner: UNT Libraries Government Documents Department

Water tolerance of aviation gasoline containing xylidines

Description: Report presenting investigations to determine the effect of xylidines on the saturation concentration of water in aviation gasoline. The saturation concentration of water in gasoline containing 0, 1, and 3 percent xylidines was determined using fresh water at two temperatures and sea water at one temperature.
Date: July 1943
Creator: Revilock, Joseph & Olson, Walter T.
Partner: UNT Libraries Government Documents Department