National Advisory Committee for Aeronautics (NACA) - 1,263 Matching Results

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Tests of Beams Having Webs With Large Circular Lightening Holes

Description: "Strength tests were made on two sets of beams having webs with large circular lightening holes. The main conclusion drawn from the tests is that allowable web stressed derived from pure shear tests and allowable flange stresses derived from compression tests cannot be applied in the design of beams without making corrections for interaction" (p. 1). Pure shear tests and beam tests were performed and the circumstances of failure were investigated.
Date: February 1944
Creator: Levin, L. Ross
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Bell XP-63 Low-Drag Wing Model With Split Flap

Description: Report presenting tests on the Bell XP-63 wing root section fitted with an 0.18c split flap hinged at approximately 0.805c on the lower surface. The tests were conducted to determine the effect of a 10 degree deflection of the split flap on the drag characteristics of the model at low lift coefficients.
Date: September 1941
Creator: Underwood, W. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Cast Aluminum-Alloy Mixed-Flow Impellers

Description: "A machined mixed-flow centrifugal impeller of a relatively complex passage shape was used as a pattern to cast a number of aluminum-alloy impellers from two aluminum-base alloys (designated alloys 1 and 2) by the 'lost wax' process. An investigation was conducted to determine whether these cast impellers, could be considered satisfactory for use in compressors. The investigation included preliminary examination, physical tests, metallurgical examination, and performance tests" (p. 1).
Date: April 1946
Creator: Douglas, John E. & Schwartz, Irving R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Exhaust Propulsion Nozzles

Description: "The thrust produced by a variety of exhaust stacks and nozzles, and the effect of these stacks and nozzles on the power of a single-cylinder R-2800 engine were investigated over a wide range of engine speeds and manifold pressures in a series of tests in the Pratt & Whitney experimental test department. From the data obtained it is possible to estimate the optimum form of nozzles and the available thrust for airplanes fitted with R-2800 engines under sea-level conditions" (p. 1).
Date: May 1943
Creator: Campbell, Paul J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Four Full-Scale Propellers to Determine the Effect of Trailing-Edge Extensions on Propeller Aerodynamic Characteristics

Description: Propellers with trailing-edge extensions were studied to determine aerodynamic characteristics. Trailing-edge extension increased power absorbed by propeller with little loss in efficiency. Power coefficient for maximum efficiency was greater for 20% camber type extension than for 20% straight type extension over range of advance ratio of 1.0 to 2.5 although camber type was less efficient. Efficiency was about the same for cruising and high-speed at a high power coefficient for propeller with e… more
Date: July 1945
Creator: Maynard, Julian D. & Evans, Albert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons

Description: Report presenting testing in the two-dimensional tunnel of four models submitted by the Glenn L. Martin Company as intermediate sections of the wing of the XB-33 airplane. Each airfoil model had different types of flaps or no flaps at all. Results regarding the lift and drag data, lift coefficients, effect of flap positions, aileron effects, drag coefficients, and hinge-moment coefficients are provided.
Date: June 1942
Creator: Abbott, Ira H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Hydraulically Expanded Rivets

Description: Report discusses the results of an investigation into the tightness, shear strength, tensile strength, and life under pulsating loads of hollow, hydraulically expanded rivets made of 17S-T aluminum alloy. The countersunk-head rivets with inserts had a much higher maximum load in shear than the modified-roundhead rivets, which did not have inserts.
Date: March 1944
Creator: Mandel, Merven W.; Crate, Harold & Schuette, Evan H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Improvements in Exhaust-Valve Performance Resulting From Changes in Exhaust-Valve and Port Design

Description: Report discusses the results of tests on single-cylinder engines to determine the worth of several changes in exhaust-valve and port design to extend the useful life of the valves used in air-cooled engines. Changes explored included the valve-head diameter, the valve-stem diameter, the valve coolant-flow area, the valve-head material, and the size of the exhaust-valve guide boss. In the normal range of temperatures encountered in engine operation, valve material was found to be the most import… more
Date: September 1945
Creator: Mulcahy, B. A. & Zipkin, M. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Inverted Spins in the NACA Free-Spinning Tunnels

Description: "Report discusses the results of inverted-spin tests in 44 airplane models in the NACA free-spinning tunnel. Spins were normally steep and recovery by rudder reversal was generally rapid. Pulling the stick back, deflecting ailerons and rudder together, and crossing them all had an effect on the amount of spin encountered and ease of recovery from spin" (p. 1).
Date: December 1943
Creator: MacDougall, George F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of NACA 65(216)-420 and 66(218)-420 Airfoils at High Speeds

Description: Report presenting wind tunnel tests of NACA 65(216)-420 and 66(218)-420 airfoils at speeds up to and slightly above the critical. Section coefficients of lift, drag, and pitching-moment and extensive pressure-distribution data are presented. The critical speed for these airfoils at their design life coefficient of 0.4 is shown to be about 460 miles per hour at seal level and about 415 miles per hour at 25,000 feet altitude.
Date: April 10, 1944
Creator: Anderson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Propeller-Speed Cooling Blowers

Description: Report presenting testing of cooling blowers for air-cooled engine installations and an exploration of the methods used in the blower design and operating characteristics of the blowers over a range of flight speeds and altitudes. The results indicate that the blowers operate as a more efficient type of propeller cuff and in many cases provide considerably more pressure boost than using a cuff.
Date: July 1942
Creator: Silverstein, Abe
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing

Description: Report presenting an investigation in the 20-foot wind tunnel to determine the drag, propulsive and net efficiencies, and cooling characteristics of several scale-model arrangements of air-cooled radial-engine nacelles and present-day propellers in front of an 18-percent-thick, 5-by-15-foot airfoil. Two 3-blade propellers with differing diameters were tested in conjunction with a 12-inch-diameter nacelle in three positions in front of the wing and with a 16-inch-diameter nacelle in six position… more
Date: September 1939
Creator: McHugh, James G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of the Jet-Motor Air-Intake Duct System on a 1/4-Scale Stub-Wing Model of a Pursuit-Type Airplane

Description: Report discussing the characteristics of the jet-motor air-intake duct system for a pursuit-type airplane with modifications to the duct system. Details of its effects on the Mach number, high pressure recovery, drag, and simplicity of the system are provided. Problems regarding the flow condition through the ducts and some potential modifications to prevent further issues are also described.
Date: May 1946
Creator: Hanson, Frederick H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of the NACA 653-018 airfoil section with boundary-layer control by suction

Description: Report presenting tests of the NACA 65(sub 3)-018 airfoil section with boundary-layer control by suction in the two-dimensional low-turbulence and two-dimensional low-turbulence pressure tunnels. Results regarding the lift characteristics, flow coefficient, maximum lift, amount of air removed by boundary-layer control, pressure distributions, and boundary layer shape are provided.
Date: October 1944
Creator: Quinn, John H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of the Northrop MX-334 Glider Airplane in the Naca Full-Scale Tunnel

Description: Report presenting tests of the Northrop MX-334 airplane in the full-scale tunnel. The results are of particular interest since the MX-334 is an all-wing glider-type airplane without a conventional fuselage or vertical surfaces. The primary purpose was to obtain sufficient data with which to determine the longitudinal and lateral stability and control characteristics of the airplane.
Date: January 1944
Creator: Brewer, Gerald W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Thermal-Electric De-Icing Equipment for Propellers

Description: "Flights were made in natural icing conditions at the NACA Ice Research Project, Minneapolis, Minn. to test several designs of thermal-electric propeller de-icing blade shoes and a hub-generator design. It was found that a minimum average unit power of 2.5 watts per square inch of blade-shoe area would protect the propeller blades at the test conditions. The most satisfactory blade shoe of the three designs tested extended to the 20-percent-chord point and to 90 percent of the blade radius" (p.… more
Date: January 1944
Creator: Scherrer, Richard & Rodert, Lewis A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A theoretical analysis of the effect of aileron inertia and hinge moment on the maximum rolling acceleration of airplanes in abrupt aileron rolls

Description: Report presenting data on the rolling accelerations of airplanes of different types and sizes in abrupt aileron rolls in connection with a number of maneuverability and flying qualities investigations. An analysis was made to determine the relation between the torque applied to the aileron system by the pilot, the motion of the system, and the subsequent rolling motion of the airplane in abrupt aileron roll.
Date: February 1942
Creator: Bailey, F. J., Jr. & O'Sullivan, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Analysis of the Lateral Stability of a Glider Towed by Twin Parallel Towlines

Description: Report discusses a theoretical analysis of the lateral stability characteristics of a glider towed by two parallel towlines, which was correlated with previously reported dynamic flight testing. The glider appears to possess sufficient stability for satisfactory pilotless towed flight. The main factors affecting stability were the dihedral angle of the glider and the length of the towlines.
Date: November 1943
Creator: Pitkin, Marvin & McKinney, Marion O., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A theoretical analysis of the performance of a diesel engine-compressor-turbine combination for aircraft

Description: Report presenting a theoretical study of a diesel engine-compressor-turbine combination for aircraft application. The performance characteristics of the compressor and turbine chosen for analysis are believed to be attainable on present aircraft equipment.
Date: April 1945
Creator: Hall, Eldon W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical and Experimental Dynamic Loads for a Prismatic Float Having an Angle of Dead Rise of 22-1/2 Degrees

Description: Report discusses the maximum load, time to reach maximum load, and variation of load with time for prismatic floats in order to improve understanding of hydrodynamic theory for the landing impact of seaplane floats. Comparison of theoretical and experimental results and their applicability to flight impact are provided.
Date: July 1945
Creator: Mayo, Wilbur L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Distribution of Load Over a Swept-Back Wing

Description: Report presenting a calculation of the load over an elliptical wing with 30 degrees sweepback by a method, based on vortex theory, which takes account of the chordwise distributions of lifting area. The theory indicates a 14-percent loss in total lift due to the introduction of sweepback, with the greatest loss taking place at the center of the span.
Date: October 1942
Creator: Cohen, Doris
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Theoretical Investigation of Longitudinal Stability of Airplanes With Free Controls Including Effect of Friction in Control System

Description: "The relation between the elevator hinge-moment parameters and the control forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance" (p. 1). Factors affecting stability positively and negatively are presented and potential modifications to the elevator control system are provided. The amount of solid friction present was found to be one of the greatest predictors of instability.
Date: February 1944
Creator: Greenberg, Harry & Sternfield, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Investigation of Methods for Computing Drag From Wake Surveys at High Subsonic Speeds

Description: Report discusses graphs of constants meant to be used with a knowledge of maximum total head loss, static-pressure decrement, and integral of total-head loss across the wake of an airfoil to determine the section profile-drag coefficient. Computations of free-stream Mach numbers for certain assumed types of total-pressure distribution in the wake are provided to compare theoretical drag coefficients as determined by other equations based on the momentum method. While some disagreements are foun… more
Date: June 1945
Creator: Heaslet, Max A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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