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  • 1
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    Traction of Pneumatic Tires on Wet Runways (1965)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: Recent work on the traction of pneumatic tires on wet runways is discussed, and it is shown that a loss of tire traction adversely affects cross-wind landings. The effect of runway surface texture is discussed,, and a simple method for measuring surface texture is described. A preliminary correlation of tire traction with surface texture is shown. Results of work at Langley Research Center on the use of air jets to improve tire traction on wet or flooded runways indicate that this is a promising approach for alleviating the large losses in tire braking and sideways traction that occur when tire hydroplaning occurs on a flooded runway.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA Conference on Aircraft Operating Problems: A Compilation of the Papers Presented; 9-17
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Considerations on a Large Hydraulic Jet Catapult (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-L51B27
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Considerations on a Large Hydraulic Jet Catapult (1954)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-3203
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental Investigation of Entrance-region Heat-transfer Coefficients (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experimental results of tests made at the Langley Memorial Aeronautical Laboratory are presented to show how heat-transfer coefficients can he increased by a method utilizing the high rate of heat transfer known to exist on any heat-transfer surface in the region adjacent to the edge on which the cooling or heating fluid impinges. The results show that, for the same pressure drop, the average surface heat-transfer.coefficient can be increased 50 to 100 percent when a cooling surface having a length of four inches in the direction of fluid flow is cut to form twenty fins with a length of 0.2 inch in the direction of fluid flow and the fins are sharpened and staggered in the air stream. The percentage of increase in the surface heat-transfer coefficient obtained as a result of shortening the length of the cooling surface varies with the pressure drop of the cooling fluid in passing the surface, the increase being largest when small pressure drop is used and smallest when high pressure drop is used.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-WR-L-239 , NACA-ARR-3K01
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experimental Verification of the Theory of Oscillating Airfoils (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements have been made of the lift on an airfoil in pitching oscillation with a continuous-recording, instantaneous-force balance. The experimental values for the phase difference between the angle of attack and the lift are shown to be in close agreement with theory.
    Type: NACA-TR-673
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Mathematical analysis of aircraft intercooler design (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mathematical analysis has been made to show the method of obtaining the dimensions of the intercooler that will use the least total power for a given set of design conditions. The results of this analysis have been used in a sample calculation and, on the basis of this calculation, a new inter cooler arrangement is suggested. Because the length of the two air passages of the new arrangement is short in comparison with the third dimension, the height of the intercooler, this intercooler arrangement has unusual dimensions. These dimensions give the proposed intercooler arrangement an advantage over one of usual dimensions because less total power will be consumed by the intercooler, the weight and volume of the intercooler will be smaller, and the pressure drop of both the engine air and the cooling air in passing through the intercooler will be lower.
    Type: NACA-TN-781
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The Pressure Available for Ground Cooling in Front of the Cowling of Air-cooled Airplane Engines (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was made of the factors affecting the pressure available for ground cooling in front of a cowling. Most of the results presented were obtained with a set-up that was about one-third full scale. A number of isolated tests on four full-scale airplanes were made to determine the general applicability of the model results. The full-scale tests indicated that the model results may be applied qualitatively to full-scale design and quantitatively as a first approximation of the front pressure available for ground cooling.
    Type: NACA-TN-673
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Charts of Pressure, Density, and Temperature Changes at an Abrupt Increase in Cross-sectional Area of Flow of Compressible Air (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-13
    Format: application/pdf
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  • 9
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    Studies of the Retardation Force Developed on an Aircraft Tire Rolling in Slush or Water (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A series of unbraked (freely rolling) taxi tests were conducted at the Langley landing-loads track with a 32 x 8.8, type 7, 22-ply-rating ribbed-tread aircraft tire to obtain data on tire retardation forces developed during rolling in both slush and water. The forward speeds of the tests ranged from 59 to 104 knots. Tire inflation pressures of 350 and 115 pounds per square inch were used. Results indicated a parabolic increase of retardation force with increasing forward velocity for both slush- and water-covered runway surfaces. The retardation force was found to increase approximately linearly with increasing water depth. Drag coefficients appropriate to the equations used are presented. Calculations made to determine the effect of slush on the take-off distance of a jet transport are in agreement with data obtained from an actual take-off in slush for this airplane. This is an interim report which deals with the effect of slush on the acceleration and the ground-run distance of airplanes during take-off.
    Keywords: Mechanical Engineering
    Type: NASA-TN-D-552 , L-1260
    Format: application/pdf
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