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 Decade: 1940-1949
 Year: 1947
 Collection: National Advisory Committee for Aeronautics Collection
Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Date: May 6, 1947
Creator: Perone, Angelo & Berthold, Cecil L.
Description: A Douglas C-74 airplane, during a test dive at about 0.525 Mach number, experienced uncontrollable longitudinal oscillations sufficient to cause shedding of the outer wing panels and the subsequent crash of the airplane. Tests of a section of the horizontal tail plane from a C-74 airplane were conducted in the Ames 16-foot high-speed wind tunnel to investigate the possibility of the tail as a contributing factor to the accident. The results of the investigations of fabric-covered elevators in various conditions of surface deformation are presented in this report.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Date: March 13, 1947
Creator: Riebe, John M. & Naeseth, Rodger L.
Description: An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of three deep-stepped planing-tail flying-boat hulls differing only in the amount of step fairing. The hulls were derived by increasing the unfaired step depth of a planing-tail hull of a previous aerodynamic investigation to a depth about 92 percent of the hull beam. Tests were also made on a transverse-stepped hull with an extended afterbody for the purpose of comparison and in order to extend and verify the results of a previous investigation. The investigation indicated that the extended afterbody hull had a minimum drag coefficient about the same as a conventional hull, 0.0066, and an angle-of-attack range for minimum drag coefficient of 0.0057 which was 14 percent less than the transverse stepped hull with extended afterbody; the hulls with step fairing had up to 44 percent less minimum drag coefficient than the transverse-stepped hull, or slightly more drag than a streamlined body having approximately the same length and volume. Longitudinal and lateral instability varied little with step fairing and was about the same as a conventional hull.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic measurements made during Navy investigation of human tolerance to wind blasts

Aerodynamic measurements made during Navy investigation of human tolerance to wind blasts

Date: March 11, 1947
Creator: Loving, Donald L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Date: April 24, 1947
Creator: Beeler, De E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Date: April 8, 1947
Creator: Foster, Gerald V.
Description: The XF-12 airplane was designed by Republic Aviation Corporation to provide the Army Air Forces with a high performance, photo reconnaissance aircraft. A series of air-stream surveys were made n the vicinity of the empennage of a 1/8.33-scale powered model of the XF-12 airplane in the Langley 19-foot pressure tunnel. Surveys of the vortical-tail region were made through a range of yaw angles of plus or minus 20 degrees at a high and low angle of attack. The horizontal-tail surveys were made over a fairly wide range of angles of attack at zero degrees yaw. Several power and flap conditions were investigated. The results are presented in the form a dynamic pressure ratios, sidewash angles, and downwash angles plotted against vertical distance from the fuselage center line. The results of the investigation indicate that a vertical tail located in a conventional position would be in a field of flow where the dynamic pressure ratios at the horizontal tail to be increased; for equal lift coefficients, the effect of power or flap deflection on the direction of flow at any particular point in the region of the horizontal tail is small.
Contributing Partner: UNT Libraries Government Documents Department
Airfoil in sinusoidal motion in a pulsating stream

Airfoil in sinusoidal motion in a pulsating stream

Date: June 1, 1947
Creator: Greenberg, J Mayo
Description: The forces and moments on a two-dimensional airfoil executing harmonic motions in a pulsating stream are derived on the basis of non-stationary incompressible potential flow theory, with the inclusion of the effect of the continuous sheet of vortices shed from the trailing edge. An assumption as to the form of the wake is made with a certain degree of approximation. A comparison with previous work applicable only to the special case of a stationary airfoil is made by means of a numerical example, and the excellent agreement obtained shows that the wake approximation is quite sufficient. The results obtained are expected to be useful in considerations of forced vibrations and flutter of rotary wing aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Altitude Cooling Investigation of the R-2800-21 Engine in the P-47G Airplane. IV - Engine Cooling-Air Pressure Distribution

Altitude Cooling Investigation of the R-2800-21 Engine in the P-47G Airplane. IV - Engine Cooling-Air Pressure Distribution

Date: January 7, 1947
Creator: Kaufman, Samuel J.; Staudt, Robert C. & Valerino, Michael F.
Description: A study of the data obtained in a flight investigation of an R-2800-21 engine in a P-47G airplane was made to determine the effect of the flight variables on the engine cooling-air pressure distribution. The investigation consisted of level flights at altitudes from 5000 to 35,000 feet for the normal range of engine and airplane operation. The data showed that the average engine front pressures ranged from 0.73 to 0.82 of the impact pressure (velocity head). The average engine rear pressures ranged from 0.50 to 0.55 of the impact pressure for closed cowl flaps and from 0.10 to 0.20 for full-open cowl flaps. In general, the highest front pressures were obtained at the bottom of the engine. The rear pressures for the rear-row cylinders were .lower and the pressure drops correspondingly higher than for the front-row cylinders. The rear-pressure distribution was materially affected by cowl-flap position in that the differences between the rear pressures of the front-row and rear-row cylinders markedly increased as the cowl flaps were opened. For full-open cowl flaps, the pressure drops across the rear-row cylinders were in the order of 0.2 of the impact pressure greater than across the front-row cylinders. Propeller speed and altitude had ...
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of R-4360-18 Power-Plant Installation for XR60 Airplane, 3, Performance of Induction and Exhaust Systems

Altitude-Wind-Tunnel Investigation of R-4360-18 Power-Plant Installation for XR60 Airplane, 3, Performance of Induction and Exhaust Systems

Date: March 26, 1947
Creator: Dupree, David T. & Hawkins, W. Kent
Description: A study has been made of the performance of the induction and the exhaust systems on the XR60 power-plant installation as part of an investigation conducted in the Cleveland altitude wind tunnel. Altitude flight conditions from 5000 to 30,000 feet were simulated for a range of engine powers from 750 to 3000 brake horsepower. Slipstream rotation prevented normal pressure recoveries in the right side of the main duct in the region of the right intercooler cooling-air duct inlet. Total-pressure losses in the charge-air flow between the turbosupercharger and the intercoolers were as high as 2.1 inches of mercury. The total-pressure distribution of the charge air at the intercooler inlets was irregular and varied as much as 1.0 inch of mercury from the average value at extreme conditions, Total-pressure surveys at the carburetor top deck showed a variation from the average value of 0.3 inch of mercury at take-off power and 0.05 inch of mercury at maximum cruising power, The carburetor preheater system increased the temperature of the engine charge air a maximum of about 82 F at an average cowl-inlet air temperature of 9 F, a pressure altitude of 5000 feet, and a brake horsepower of 1240.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines, 4, Analysis of Compressor Performance

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines, 4, Analysis of Compressor Performance

Date: April 4, 1947
Creator: Dietz, Robert O. & Kuenzig, John K.
Description: Investigations were conducted in the Cleveland altitude wind tunnel to determine the performance and operational characteristics of the 19B-2, 19B-8, and 19XS-1 turbojet engines. One objective was to determine the effect of altitude, flight Mach number, and tail-pipe-nozzle area on the performance characteristics of the six-stage and ten-stage axial-flow compressors of the 19B-8 and 19XB-1 engines, respectively, The data were obtained over a range of simulated altitudes and flight Mach numbers. At each simulated flight condition the engine was run over its full operable range of speeds. Performance characteristics of the 19B-8 and 19XB-1 compressors for the range of operation obtainable in the turboJet-engine installation are presented. Compressor characteristics are presented as functions of air flow corrected to sea-level conditions, compressor Mach number, and compressor load coefficient. For the range of compressor operation investigated, changes in Reynolds number had no measurable effect on the relations among compressor Mach number, corrected air flow, compressor load coefficient, compressor pressure ratio, and compressor efficiency. The operating lines for the 19B-8 compressor lay on the low-air-flow side of the region of maximum compressor efficiency; the 19B-8 compressor operated at higher average pressure coefficients per stage and produced a lower over-all pressure ratio than did ...
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet-Propulsion Engines. II - Analysis of Turbine Performance of the 19B-8 Engine

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet-Propulsion Engines. II - Analysis of Turbine Performance of the 19B-8 Engine

Date: January 8, 1947
Creator: Krebs, Richard P. & Suozzi, Frank L.
Description: Performance characteristics of the turbine in the 19B-8 jet propulsion engine were determined from an investigation of the complete engine in the Cleveland altitude wind tunnel. The investigation covered a range of simulated altitudes from 5000 to 30,000 feet and flight Mach numbers from 0.05 to 0.46 for various tail-cone positions over the entire operable range of engine speeds. The characteristics of the turbine are presented as functions of the total-pressure ratio across the turbine and the turbine speed and the gas flow corrected to NACA standard atmospheric conditions at sea level. The effect of changes in altitude, flight Mach number, and tail-cone position on turbine performance is discussed. The turbine efficiency with the tail cone in varied from a maximum of 80.5 percent to minimum of 75 percent over a range of engine speeds from 7500 to 17,500 rpm at a flight Mach number of 0.055. Turbine efficiency was unaffected by changes in altitude up to 15,000 feet but was a function of tail-cone position and flight Mach number. Decreasing the tail-pipe-nozzle outlet area 21 percent reduced the turbine efficiency between 2 and 4.5 percent. The turbine efficiency increased between 1.5 and 3 percent as the flight Mach number ...
Contributing Partner: UNT Libraries Government Documents Department
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine II : performance with water injection at compressor inlet

Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine II : performance with water injection at compressor inlet

Date: May 19, 1947
Creator: Dietz, Robert O & Fleming, William A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine III : performance with tail-pipe burning in standard-size tail pipe

Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine III : performance with tail-pipe burning in standard-size tail pipe

Date: August 11, 1947
Creator: Fleming, William A & Golladay, Richard L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of airspeeds and Mach numbers attained by Lockheed Constellation airplanes in transcontinental operations during the early summer of 1946

An analysis of airspeeds and Mach numbers attained by Lockheed Constellation airplanes in transcontinental operations during the early summer of 1946

Date: October 10, 1947
Creator: Steiner, Roy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of jet-propulsion-engine combustion-chamber pressure losses

Analysis of jet-propulsion-engine combustion-chamber pressure losses

Date: January 1, 1947
Creator: Pinkel, I Irving & Shames, Harold
Description: The development and the use of a chart for estimating the pressure losses in jet-engine combustion chambers are described. By means of the chart, the pressure losses due to fluid friction and to momentum changes in the air flow accompanying combustion can be separately evaluated. The pressure-loss chart is based on the assumption that the pressure losses in the actual combustion chamber can be matched by those of an equivalent combustion chamber of constant cross-sectional area. The concept of the equivalent combustion chamber serves as a convenient basis for comparing the pressure-loss characteristics of combustion chambers of a variety of designs. The over-all pressure losses computed from the pressure-loss chart are within 7 percent of the experimental values for the three types of combustion chambers considered herein.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane

An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane

Date: September 25, 1947
Creator: Brown, Harvey H; Rolls, L Stewart & Clousing, Lawrence A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Date: January 1, 1947
Creator: Goldstein, Arthur W
Description: The performance of the turbine component of an NACA research jet engine was investigated with cold air. The interaction and the matching of the turbine with the NACA eight-stage compressor were computed with the combination considered as a jet engine. The over-all performance of the engine was then determined. The internal aerodynamics were studied to the extent of investigating the performance of the first stator ring and its influence on the turbine performance. For this ring, the stream-filament method for computing velocity distribution permitted efficient sections to be designed, but the design condition of free-vortex flow with uniform axial velocities was not obtained.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Date: October 1, 1947
Creator: Goldstein, Arthur W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the compressive strength of honeycomb cores for sandwich construction

An analysis of the compressive strength of honeycomb cores for sandwich construction

Date: January 1, 1947
Creator: Norris, Charles B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the factors that affect the exhaust process of a four-stroke-cycle reciprocating engine

An analysis of the factors that affect the exhaust process of a four-stroke-cycle reciprocating engine

Date: April 1, 1947
Creator: Stanitz, John D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Analysis of the Full-Floating Journal Bearing

An Analysis of the Full-Floating Journal Bearing

Date: January 28, 1947
Creator: Shaw, M.C. & Nussdorfer, T.J.
Description: An analysis of the operating characteristics of a full-floating bearing - a bearing in which a floating sleeve is located between the journal and bearing surfaces - is presented together with charts - from which the performance of such bearings may be predicted. Examples are presented to illustrate the use of these charts and a limited number of experiments conducted upon a glass full-floating bearing to verify some results of the analysis are reported. The floating sleeve can operate over a wide range of speeds for a given shaft speed, the exact value depending principally upon the ratio of clearances and upon the ratio of radii of the bearing. Lower operating temperatures at high rotative speeds are to be expected by using a full-floating bearing. This lower operating temperature would be obtained at the expense of the load-carrying capacity of the bearing if, for comparison, the clearances remain the same in both bearings. A full-floating bearing having the same load capacity as a conventional journal bearing may be designed if decreased clearances are allowable.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the full-floating journal bearing

An analysis of the full-floating journal bearing

Date: January 1, 1947
Creator: Shaw, M C & Nussdorfer, T J , Jr
Description: An analysis of the operating characteristics of a full-floating journal bearing, a bearing in which a floating sleeve is located between the journal and bearing surfaces, is presented together with charts from which the performance of such bearings may be predicted. Examples are presented to illustrate the use of these charts and a limited number of experiments conducted upon a glass full-floating bearing are reported to verify some results of the analysis.
Contributing Partner: UNT Libraries Government Documents Department
Analysis, Verification, and Application of Equations and Procedures for Design of Exhaust-Pipe Shrouds

Analysis, Verification, and Application of Equations and Procedures for Design of Exhaust-Pipe Shrouds

Date: December 1, 1947
Creator: Ellerbrock, Herman H.; Wcislo, Chester R. & Dexter, Howard E.
Description: Investigations were made to develop a simplified method for designing exhaust-pipe shrouds to provide desired or maximum cooling of exhaust installations. Analysis of heat exchange and pressure drop of an adequate exhaust-pipe shroud system requires equations for predicting design temperatures and pressure drop on cooling air side of system. Present experiments derive such equations for usual straight annular exhaust-pipe shroud systems for both parallel flow and counter flow. Equations and methods presented are believed to be applicable under certain conditions to the design of shrouds for tail pipes of jet engines.
Contributing Partner: UNT Libraries Government Documents Department
Analytical and experimental investigation of bolted joints

Analytical and experimental investigation of bolted joints

Date: October 1, 1947
Creator: Rosenfeld, Samuel J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical comparison of a standard turbojet engine, a turbojet engine with a tail-pipe burner, and a ram-jet engine

Analytical comparison of a standard turbojet engine, a turbojet engine with a tail-pipe burner, and a ram-jet engine

Date: February 10, 1947
Creator: Krebs, Richard P & Palasics, John
Description: None
Contributing Partner: UNT Libraries Government Documents Department