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Performance of the 19XB 10-Stage Axial-Flow Compressor

Description: The 19xB compressor, which replaces the 19B compressor and has the same length and diameter 88 the 19B compressor, was designed with 10 stages to deliver 30 pounds of air per second for a pressure ratio of 4.17 at an equivalent speed of 17,000 rpm; the 19B was designed with six stages for a pressure ratio of 2.7 at the same weight flow and speed as the 19XB compressor. The performance characteristics of the new compressor were determined at the NACA Cleveland laboratory at the request of the Bu… more
Date: December 30, 1946
Creator: Downing, Richard M. & Finger, Harold B.
Partner: UNT Libraries Government Documents Department
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Characteristics of a Hot Jet Discharged from a Jet-Propulsion Engine

Description: From Summary: "An investigation of a heated jet was conducted in conjunction with tests of an axial-flow jet-propulsion engine in the Cleveland altitude wind tunnel. Pressure and temperature surveys were made across the jet 10 and 15 feet behind the jet-nozzle outlet of the engine. Surveys were obtained at pressure altitudes of 10,000, 20,000, 30,000, and 40,000 feet with test-section velocities from 30 to 110 feet per second and test-section temperatures from 60 F to -50 F. From measurements t… more
Date: December 27, 1946
Creator: Fleming, William A.
Partner: UNT Libraries Government Documents Department
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Performance of 19XB-2A Gas Turbine 1 - Effect of Pressure Ratio and Inlet Pressure on Turbine Performance for an Inlet Temperature of 800 Degrees R

Description: "An investigation of the 19XB-2A gas turbine is being conducted at the Cleveland laboratory to determine the effect on turbine performance of various inlet pressures, inlet temperatures, pressure ratios, and wheel speeds. The engine of which this turbine is a component is designed to operate at an air flow of 30 pounds per second at a compressor rotor speed of 17,000 rpm at sea-level conditions. At these conditions the total-pressure ratio is 2.08 across the turbine and the turbine inlet total … more
Date: December 26, 1946
Creator: Kohl, Robert C. & Larkin, Robert G.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a Modified Koppers Aeromatic Impeller-Generator Combination, TED No. NACA ARR 2901

Description: From Summary: "An investigation was conducted in the 6- by 6-foot test section of the Langley stability tunnel on a modified Koppers Aeromatic wind-driven impeller-generator combination. This investigation consisted of a few fixed pitch tests and a series of variable pitch tests. The fixed pitch tests indicated that the impeller should operate between the blade-pitch angles of 20 and 32deg at the specified output of 11.7 kilowatts in order to remain within the specified rotational speed of from… more
Date: December 26, 1946
Creator: Queijo, M. J.
Partner: UNT Libraries Government Documents Department
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Investigation of Operating Characteristics of an Engine Equipped with Modifications to Eliminate Fuel-Evaporation Icing

Description: From Summary: "Two modified fuel-injection systems, a drilled-inducer type and a spinner type, that prevent serious fuel-evaporation icing were installed on a V-type, liquid-cooled aircraft engine and a preliminary investigation was conducted to determine the effect on engine operating characteristics. The spinner system was also ground - and flight tested on a twin-engine fighter airplane. Flight measurements of cylinder-head temperature over a range of fuel-air ratios and engine power conditi… more
Date: December 24, 1946
Creator: Mulholland, Donald R. & Zlotowski, Edward D.
Partner: UNT Libraries Government Documents Department
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Fabrication of Ceramic Shapes

Description: Abstract: "This report indicates some of the methods employed at Los Alamos for the fabrication of refractory products."
Date: December 23, 1946
Creator: Mullen, Terence & Taub, James M.
Partner: UNT Libraries Government Documents Department
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Voltage Regulator for Electroplating Control

Description: This report describes an instrument used for electrolytic separation. It was one of four instruments previous used and improved, yet lacked details until now. The instrument's design and operation is described herein.
Date: December 23, 1946
Creator: Rogers, Lockhard Burgess & Pickle, C. B.
Partner: UNT Libraries Government Documents Department
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Method for calculating wing characteristics by lifting-line theory using nonlinear section lift data

Description: "A method is presented for calculating wing characteristics by lifting-line theory using nonlinear section lift data. Material from various sources is combined with some original work into the single complete method described. Multhopp's systems of multipliers are employed to obtain the induced angle of attack directly from the spanwise lift distribution. Equations are developed for obtaining these multipliers for any even number of spanwise stations, and values are tabulated for 10 stations al… more
Date: December 20, 1946
Creator: Sivells, James C. & Neely, Robert H.
Partner: UNT Libraries Government Documents Department
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Performance of the Modified V-1710-93 Engine-Stage Supercharger with a Constant-Area Vaneless Diffuser

Description: "As part of an investigation to increase the power output of the V-1710-93 engine at altitude, the engine-stage supercharger was combined with a constant-area vaneless diffuser designed to improve the performance of the engine-stage supercharger at the rated engine operating point. The performance of the modified supercharger was investigated in a variable-component supercharger test rig and compared with that of the standard supercharger with an 8-vaned diffuser. A separate evaluation of the c… more
Date: December 20, 1946
Creator: Douglas, John E. & Schwartz, Irving R.
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings 6 - Hamilton Standard 6507A-2 Four- and Three-Blade Propellers

Description: "An altitude-wind-tunnel investigation has been made to determine the performance of Hamilton Standard 6507A-2 four-blade and three-blade propellers on a YP-47M airplane at high blade loadings and high engine powers. Characteristics of the four-blase propeller were obtained for a range of power coefficients from 0.10 to 1.00 at free-stream Mach numbers of 0.20, 0.30, 0.40. Characteristics of the three-blade propeller were obtained for a range of power coefficients from 0.30 to 1.00 at a free-st… more
Date: December 19, 1946
Creator: Saari, Martin J. & Sorin, Solomon M.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Icing and Heated-Air De-Icing Characteristics of the R-2600-13 Induction System

Description: "A laboratory investigation was made on a Holley 1685-HB carburetor mounted on an R-2600-13 supercharger assembly to determine the icing characteristics and the heated-air de-icing requirements of this portion of the B-25D airplane induction system. Icing has been found to be most prevalent at relatively small throttle openings and, consequently, all runs were made at simulated 60-percent normal rated power condition. Icing characteristics were determined during a series of 15-minute runs over … more
Date: December 19, 1946
Creator: Chapman, Gilbert E.
Partner: UNT Libraries Government Documents Department
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Resume of Wind-Tunnel Data on the Effect of External Stores on Stability of Models of Military Airplanes

Description: Report presenting a study of static wind-tunnel data on the effects of external stores like tanks, torpedoes, bombs, and radar domes on the stability of military airplanes. The results are focused on longitudinal and lateral stability. Static longitudinal stability is affected at various Mach numbers, but the data was not sufficient to estimate the effect on the lateral stability.
Date: December 19, 1946
Creator: Silvers, H. Norman & Vogler, Raymond D.
Partner: UNT Libraries Government Documents Department
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Crystal Densities of Uranium Chlorides

Description: Abstract: "Using xylene as the densimetric solvent, the crystal densities have been determined by the pyknometric method for the following chlorides, UCl3, UCl4, UCl6(UCl4), UCl6 and U02Cl2."
Date: December 13, 1946
Creator: Sterett, C. C. & Calkins, V. P.
Partner: UNT Libraries Government Documents Department
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Knock-Limited Performance of Triptane and Xylidines Blended with 28-R Aviation Fuel at High Compression Ratios and Maximum-Economy Spark Setting

Description: From Summary :"An investigation was conducted to evaluate the possibilities of utilizing the high-performance characteristics of triptane and xylidines blended with 28-R fuel in order to increase fuel economy by the use of high compression ratios and maximum-economy spark setting. Full-scale single-cylinder knock tests were run with 20 deg B.T.C. and maximum-economy spark settings at compression ratios of 6.9, 8.0, and 10.0, and with two inlet-air temperatures. The fuels tested consisted of tri… more
Date: December 12, 1946
Creator: Held, Louis F. & Pritchard, Ernest I.
Partner: UNT Libraries Government Documents Department
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Evaluation of Gust and Draft Velocities from Flights of P-61c Airplanes within Thunderstorms August 7, 1946 to August 13, 1946 at Orlando, Florida

Description: This report presents the results obtained from gust and draft velocity measurements within thunderstorms for the period August 7, 1946 to August, 13, 1946 at Orlando Florida. In several of the surveys, indications of ambient air temperature were obtained from photo-observer records. These data are summarized in the report.
Date: December 9, 1946
Creator: Tolefson, Harold B.
Partner: UNT Libraries Government Documents Department
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Spectrophotometric Evidence for the Existence of UCl₅ as the Double Compound UCl₆ and UCl₄

Description: Abstract: "Spectrophotometric evidence for the existence of UCl₅ as a double compound UCl₆ and UCl₄ has been obtained by studying the absorption spectra of these chlorides in CCl₄ and SOCl2 solutions in the visible and ultraviolet regions of the spectrum."
Date: December 9, 1946
Creator: Sterett, C. C. & Calkins, V. P.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-3 Airplane

Description: "Because previous work has indicated that jettisonable nose sections of airplanes may be inherently unstable, and thus may cause dangerous centripetal accelerations on a pilot after jettisoning during high-speed flight, an investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the behavior in descent of a model of the jettisonable nose section of the Douglas X-3 airplane. The effects of varying the center-of-gravity position, of attaching fins of various sizes… more
Date: December 8, 1946
Creator: Scher, Stanley H.
Partner: UNT Libraries Government Documents Department
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Effect of Three Modifications on Performance of Auxiliary-Stage Supercharger for V-1710-93 Engine

Description: "Three modifications of the auxiliary-stage supercharger for the V-1710-93 engine were designed and tested as part of an investigation to improve the power output and the altitude performance of the engine. A 12-vane diffuser was substituted for the standard 11-vane diffuser, and a vaneless discharge passage and a modified scroll were designed to increase the flow capacity of the supercharger and thereby to increase the performance at the high volume flows required by the engine. With the 12-va… more
Date: December 6, 1946
Creator: Downing, Richard M. & Finger, Harold B.
Partner: UNT Libraries Government Documents Department
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Theoretical and Experimental Data for a Number of NACA 6A-Series Airfoil Sections

Description: The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is characteristic of the NACA 6-series sections. Theoretical data are presented for NACA 6A-series basic thickness forms having the position of minimum pressure at 30-, 40-, and 50-percent chord and with thickness ratios varying from 6 percent to 15 percent. Also presented are data for a mean line designed to maintain straight sides on the cambered sections. The experimental results of a two dimensional … more
Date: December 6, 1946
Creator: Loftin, Laurence K., Jr.
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Tests of a 1/26th Scale Model of the Douglas XTB2D-1 Airplane

Description: "A spin-tunnel investigation of a 1/26 scale model of the Douglas XTB2D-1 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements upon the erect- and inverted-spin and recovery characteristics of the model were determined for various loading conditions. Tests were also performed to determine the effects of various tail modifications. The investigation included emergency spin-recovery parachute tests as well as crew-escape and rudder… more
Date: December 5, 1946
Creator: Stone, Ralph W., Jr. & Berman, Theodore
Partner: UNT Libraries Government Documents Department
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Tank Tests of a 1/7-Size Powered Dynamic Model of the Grumman XJR2F-1 Amphibian: Spray Characteristics, Take-Off and Landing Stability in Smooth Water - Langley Tank Model 212, TED No. NACA 2378

Description: From Summary: "Tests of a model of the XJR2F-Y amphibian were made in Langley tank no. to determine the spray characteristics and the take-off and landing stability. At a gross load of 22,000 pounds full size, spray entered the propeller disk only at a very narrow range of speeds. The spray striking the flaps was not excessive and no appreciable wetting of the tail surfaces was noted. The trim limits of stability appeared to be satisfactory and the upper-limit porpoising was not violent."
Date: December 4, 1946
Creator: Land, Norman S. & Zeck, Howard
Partner: UNT Libraries Government Documents Department
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Ditching Tests of a 1/9-Size Model of the Army P-38 Airplane in Langley Tank No. 2 and at the Outdoor Catapult

Description: "A dynamically similar model of the Army P-38 airplane was tested to determine the best way to land this airplane on the water and to determine its probable ditching performance. The tests consisted of ditching the model at various landing attitudes, flap settings, speeds, weights, and conditions of simulated damage. The model was ditched in calm water from the tank towing carriage and a few ditching were made in both calm and rough water at the outdoor catapult" (p. 1).
Date: December 3, 1946
Creator: Jarvis, George A. & Cederborg, Gibson A.
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Directional Stability and Control of a P-51D Airplane with a Horn-Balanced Rudder as Compared with Previously Tested Vertical-Tail Configurations

Description: "At the request of the Air Materiel Command, Army Air Forces, flight tests were conducted on a P-5lD-20-NA (AAF No. 44-63826) airplane equipped with a horn-balanced rudder. This rudder was fitted with an unbalancing tab as was the original product fan rudder. Tests were made both with the unbalancing tab in operation and with the unbalancing tab locked. The modification to the original vertical tail consisted of removing the cap from the top of the fin and adding 1.91 square feet of area to the… more
Date: December 3, 1946
Creator: Mungall, Robert G.
Partner: UNT Libraries Government Documents Department
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