UNT Libraries Government Documents Department - 18 Matching Results

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Estimates of the Vertical-Tail Loads of a Bell P-63A-1 Airplane (AAF No. 42-68889) in Accelerated Rolling Maneuvers Based on Flight Tests With Two Vertical-Tail Arrangements

Description: Report discussing the results of using an enlarged vertical tail on a P-63A-1 on directional stability. The tests included measurements of the amount of sideslip at various speeds and normal accelerations. Potential required modifications for increased performance using the larger tail are also described.
Date: November 30, 1944
Creator: Johnson, Harold I.
Item Type: Refine your search to only Report
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Tests of a 0.1475c Aileron With a Tab on Low-Drag Section for Curtiss XP-60 Airplane in the Low-Turbulence Tunnel

Description: "Preliminary two-dimensional tests of the hinge-moment characteristics of a 0.1725c internally balanced aileron on the subject XP-60 wing section indicated that more internal balance would be required if light stick forces were to be obtained at high speeds. The present series of tests were therefore undertaken in order to investigate methods of reducing the slope of the hinge-moment curve while still maintaining the required aileron effectiveness" (p. 1).
Date: November 1941
Creator: von Doenhoff, A. E. & Underwood, W. J.
Item Type: Refine your search to only Report
open access

An Investigation of the Mutual Interference Effects of a Tail-Surface: Stern Propeller Installation on a Model Simulating the Douglas XB-42 Empennage

Description: Report discussing the mutual interference effects of tail surfaces and a stern propeller on a model of the XB-42.The main focus was to determine the effect of tail surface-propeller spacing upon the periodic tail surface loading coincident with propeller blade passage.
Date: November 9, 1944
Creator: Bartlett, Walter A., Jr. & Marino, Alfred A.
Item Type: Refine your search to only Report
open access

Aerodynamic Tests of an NACA 66(215)-116, a=0.6 Airfoil With a 0.25c Slotted Flap for the Fleetwings XA-39 Airplane

Description: Report presenting testing in the two-dimensional low-turbulence tunnels on a 24-inch-chord model of the NACA 66(215)-116 a = 0.6 airfoil with a 0.25-chord slotted flap. The optimum flap pivot positions were found for three different conditions. The conditions were determined from a consideration of the landing, take-off, and strafing requirements of the airplane.
Date: November 1944
Creator: Cahill, Jones F.
Item Type: Refine your search to only Report
open access

Control-Motion Studies of the PBM-3 Flying Boat in Abrupt Pull-Ups

Description: Report presenting a control-motion study in flight that is part of series covering a range of types and sizes of modern airplanes. This particular one involves the PBM-3 flying boat, which is equipped with a control mechanism typical of the cable-type systems in large transport, cargo, or bomber airplanes as well as those employed in flying boats. The elasticity of the elevator control system of the PBM-3 was such to limit the obtainable acceleration to about 3g for center-of-gravity positions … more
Date: November 1942
Creator: Pearson, Henry A. & Smull, Leland K.
Item Type: Refine your search to only Report
open access

Cooling Investigation of a B-24D Engine-Nacelle Installation in the NACA Full-Scale Tunnel

Description: Report presenting an investigation conducted in the full-scale tunnel to determine methods of improving the cooling of the B-24D engine installation. The B-24D is a four-engine high-wing monoplane having a span of 110 feet, a wing area of 1048 square feet, and a gross weight of 56,000 pounds.
Date: November 1942
Creator: Lehr, Robert R.; Kinghorn, George F. & Guryansky, Eugene R.
Item Type: Refine your search to only Report
open access

Heat-Transfer Tests of a Steel Cylinder Barrel With Aluminum Fins of Optimum Proportions

Description: Report presenting testing of a steel cylinder barrel with aluminum fins of the optimum spacing of 0.090 inch. The primary purpose is to determine the excellence of the thermal bonds between the aluminum fins and the aluminum base and between the aluminum base and the steel and to compare the heat transfer of the barrel with that of barrels with a fin space of 0.052 inch.
Date: November 1940
Creator: Ellerbrock, Herman H., Jr. & Mann, Alvin H.
Item Type: Refine your search to only Report
open access

Flying Qualities of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage as Estimated From Wind-Tunnel Tests of a 1/8-Scale Powered Model

Description: Report discussing the flying qualities of a high-speed bomber with a dual pusher propeller aft of the empennage. The airplane was found to have satisfactory flying qualities except for stability issues with aft center of gravity, high elevator control forces in landing, insufficient elevator control in take-off, and low rudder-free directional stability.
Date: November 4, 1944
Creator: Weiberg, James A. & Schnurbusch, Alfred W.
Item Type: Refine your search to only Report
open access

Vibration-Response Tests of a 1/5-Scale Model of the Grumman F6F Airplane in the Langley 16-Foot High-Speed Tunnel

Description: Report discussing vibration experiments on a model of the Grumman F6F at up to 500 miles per hour. There was no indication of actual flutter by shift or frequencies or by decreasing dampening. The symmetrical and unsymmetrical bending frequencies and responses are provided.
Date: November 18, 1944
Creator: Theodorsen, Theodore & Regier, Arthur A.
Item Type: Refine your search to only Report
open access

Lateral-control characteristics of North American XP-51 airplane (A. C. No. 41-38) with beveled trailing-edge ailerons in high-speed flight

Description: Report presenting the flight tests of beveled trailing-edge ailerons on the North American XP-51 airplane which were extended to determine the aileron characteristics in high-speed dives. Standard recording instruments were used to determine airspeed, aileron position, stick force, and rate of roll. The results show that the beveled trailing-edge form of aerodynamic balance had no abnormal or unusual characteristics in high-speed flight.
Date: November 1942
Creator: Hoover, Herbert H. & White, Maurice D.
Item Type: Refine your search to only Report
open access

Tests of an Attack-Type Airplane in the Ames 40- by 80-Foot Wind Tunnel to Improve the High-Speed Maneuvering Control-Force Characteristics

Description: Report discussing testing on a twin-engine airplane to determine which modifications would make it suitable for ground-support attack operations. Some of the suggested modifications include replacing fabric-covered elevators with metal-covered elevators with a balance tab, replacing fabric-covered ailerons with metal-covered ailerons with a balance tab, sealing the airplane, fairing the nose guns, removing the lower-periscope deflector, and fairing the bomb racks. The results of other types of … more
Date: November 1945
Creator: McCormack, Gerald M.
Item Type: Refine your search to only Report
open access

Ditching tests with a 1/10-size model of the Army A-20A airplane in Langley tank no.2 and on an outdoor catapult

Description: Testing of a dynamically similar model of an Army A-20A airplane to determine the best way to land the airplane in calm and rough water and to determine its probable ditching performance. Results regarding the effect of speed and attitude, effect of flap setting, effect of wind and seaway, effect of simulated damage, effect of sinking speed, effect of propellers, effect of gun blisters, and effect of weight are provided.
Date: November 1944
Creator: Jarvis, George A. & Steiner, Margaret F.
Item Type: Refine your search to only Report
open access

Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Cantilever Beam With a Mass at Its Tip

Description: Report discusses an investigation into the behavior of a cantilever beam in transverse motion with a mass at its tip when the root is suddenly brought to rest. Equations for determining the stresses, deflections, and accelerations that arise in the beam are also provided. This testing can be applied to the shock created in an airplane when landing and the vibrations that result.
Date: November 1944
Creator: Stowell, Elbridge Z.; Schwartz, Edward B.; Houbolt, John C. & Schmieder, Albert K.
Item Type: Refine your search to only Report
open access

F-3 and F-4 Engine Tests of Several High-Antiknock Components of Aviation Fuel

Description: Report discussing testing on triptane, hot-acid octane, diisopropyl, neohexane, mixed xylenes, cumene, benzene, toluene, and methyl tert-butyl ether in several blends to determine their knock-limited performance data in F-3 and F-4 engines at standard operating conditions. All of the blending agents examined were found to be usable, with concentrations varying depending on various thermodynamic properties.
Date: November 27, 1944
Creator: Imming, Harry S.; Barnett, Henry C. & Genco, Russell S.
Item Type: Refine your search to only Report
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