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  • Cell & Developmental Biology  (108)
  • Aerodynamics  (13)
  • Aircraft Propulsion and Power  (3)
  • Seismology  (3)
  • 1940-1944  (127)
  • 1935-1939
  • 1943  (127)
Collection
Keywords
Publisher
Years
  • 1940-1944  (127)
  • 1935-1939
Year
  • 1
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    NACA Investigation of a Jet-Propulsion System Applicable to Flight (1943)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Following a brief history of the NACA investigation of jet propulsion, a discussion is given of the general investigation and analysis leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made.
    Keywords: Aircraft Propulsion and Power
    Type: NACA/TR-802
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2. At high Mach numbers pronounced decrease of the maximum lift coefficient was found. The magnitude of the effects of compressibility on the maximum lift coefficient and the low speeds at which these effects first appear indicate clearly that consideration of the take-off thrust for propellers will give results seriously in error if these considerations are based on the usual low-speed maximum-lift-coefficient data generally used.
    Keywords: Aerodynamics
    Type: NACA-ACR-246 , NACA-SR-246
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It i s shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients . The available data indicate that for low-drag and high critical compressibility speed airfoils and bodies of revolution, this effect is favorable.
    Keywords: Aerodynamics
    Type: NACA-ACR-252 , NACA-SR-252
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Limitations of Lifting-Line Theory for Estimation of Aileron Hinge-Moment Characteristics (1943)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Hinge-moment parameters for several typical ailerons were calculated from section data with the aspect-ratio correction as usually determined from lifting-line theory. The calculations showed that the agreement between experimental and calculated results was unsatisfactory. An additional aspect-ratio correction, calculated by the method of lifting-surface theory, was applied to the slope of the curve of hinge-moment coefficient against angle of attack at small angles of attack. This so-called streamline-curvature correction brought the calculated and experimental results into satisfactory agreement.
    Keywords: Aerodynamics
    Type: AD-A801563 , NACA-WR-L-281 , NACA-CB-3L02
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing than for a 10 in. rib spacing.
    Keywords: Aerodynamics
    Type: NACA-WR-L-416
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Wind-Tunnel Investigation of a Revised Horizontal Tail Surface for the Grumman TBF-1 Airplane (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-WR-L-702
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Drag Measurements of a Protruding .50-caliber Machine Gun with Barrel Jacket Removed (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made in 8-ft high-speed wind tunnel to determine the drag reduction possible by eliminating the barrel jacket of a protruding 50-caliber aircraft gun. It was found that the drag of a standard aircraft gun protruding into the air stream at right angles to the flow can be reduced by 23% by discarding the barrel jacket. At 300 mph and sea-level conditions, this amounts to a decrease in drag of from 83 to 64 pounds. A rough surface finish on the barrel was found to have no adverse effects on the drag of the barrel, the drag being actually less at high Mach Numbers.
    Keywords: Aerodynamics
    Type: NACA-WR-L-581
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Operating Temperatures of a Sodium-Cooled Exhaust Valve as Measured by a Thermocouple (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A thermocouple was installed in the crown of a sodium-cooled exhaust valve. The valve was then tested in an air-cooled engine cylinder and valve temperatures under various engine operating conditions were determined. A temperature of 1337 F was observed at a fuel-air ratio of 0.064, a brake mean effective pressure of 179 pounds per square inch, and an engine speed of 2000 rpm. Fuel-air ratio was found to have a large influence on valve temperature, but cooling-air pressure and variation in spark advance had little effect. An increase in engine power by change of speed or mean effective pressure increased the valve temperature. It was found that the temperature of the rear spark-plug bushing was not a satisfactory indication of the temperature of the exhaust valve.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-140 , NACA-ARR-3L06
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Flight Tests of Various Tail Modifications on the Brewster XSBA-1 Airplane II : Measurements of Flying Qualities with Tail Configuration Number Two (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several tail modifications of the Brewster XSBA-1 scout-bomber were investigated and results compared. Modifications consisted of variation of the chord of the elevator and rudder while the total area of the surfaces is kept constant and variations of the total area of the vertical tail surface. Configuration number 2 reduced trim changes by 50 percent and reduced average elevator control force gradient from 30 to 27 pounds/g. Stick travel required to stall in maneuver was 4.6 inches.
    Keywords: Aerodynamics
    Type: NACA-WR-L-598
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    The Measurement of Fuel-Air Ratio by Analysis for the Oxidized Exhaust Gas (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made to determine a method of measuring fuel-air ratio that could be used for test purposes in flight and for checking conventional equipment in the laboratory. Two single-cylinder test engines equipped with typical commercial engine cylinders were used. The fuel-air ratio of the mixture delivered to the engines was determined by direct measurement of the quantity of air and of fuel supplied and also by analysis of the oxidized exhaust gas and of the normal exhaust gas. Five fuels were used: gasoline that complied with Army-Navy fuel Specification No. AN-VV-F-781 and four mixtures of this gasoline with toluene, benzene, and xylene. The method of determining the fuel-air ratio described in this report involves the measurement of the carbon-dioxide content of the oxidized exhaust gas and the use of graphs for the presented equation. This method is considered useful in aircraft, in the field, or in the laboratory for a range of fuel-air ratios from 0.047 to 0.124.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-757
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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