17 research outputs found
The Belt Method for Measuring Pressure Distribution
The measurement of pressure distribution may be accomplished rapidly for any number of locations deemed necessary in model or full-scale investigations by use of the "belt" method. Reasonable accuracy may be obtained by careful use of this method
Static Thrust of an Annular Nozzle with a Concave Central Base
A static test of an annular nozzle with a concave central base, producing a jet in which tangents to the jet streamlines at the exit converged toward a region on the axis of symmetry downstream of the exit, has indicated good thrust performance. A value of nozzle-flow coefficient only slightly less than unity indicates the internal loss to be small. Pressures on the concave central base are relatively large and positive, and a predictable portion of the total thrust of the jet is exerted on the central base
The Langley 2,000-horsepower Propeller Dynamometer and Tests at High Speed of an NACA 10-(3)(08)-03 Two-blade Propeller
This paper contains a detailed description of a 2,000-horsepower propeller dynamometer used to make wind-tunnel tests of a two-blade NACA 10-(3)(08)-03 propeller for a range of blade angles from 20 degrees to 55 degrees at airspeeds up to 500 miles per hour. The results of these tests and comparisons with results obtained from a theoretical analysis and from previous tests made in other wind tunnels are presented
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NACA Advanced Restricted Reports
From Introduction: "The purpose of this report is to show that it is practical to apply a least-squares method to the correlation of engine-cooling data.
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NACA Restricted Bulletins
"The measurement of pressure distribution may be accomplished rapidly for any number of locations deemed necessary in model or full-scale investigations by use of the 'belt' method. Reasonable accuracy may be obtained by careful use of this method" (p. 1)
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NACA Memorandum Reports
Report presenting static tests on four full-scale two-bladed propellers differing only in blade sections at blade angles from 0 to 20 degrees at the three-quarters radius. Two of the propellers were also tested as three-bladed propellers. For all of the propellers tested, the highest value of the static thrust figure of merit occurred at a tip-speed ratio between 0.7 and 0.9; the highest efficiency in flight may be expected in the same range of tip-speed ratios
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NACA Special Reports
Report discusses the design of a cooling system developed for a Pratt & Whitney H-2800 engine equipped with a two-stage supercharger. The wing-duct system was newly developed and was determined to be a valuable method for cooling engine auxiliaries by combining simplicity with low drag and excellent cooling capabilities
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NACA Technical Notes
Testing of a 10-foot-diameter three-blade Curtiss 89301-15 propeller with Clark Y blade sections was conducted in the 16-foot high-speed tunnel to determine the effect of simulated ice on the aerodynamic characteristics of the propeller. The propellers were tested on a 2000-horsepower dynamometer at rotational speed 1800 rpm at several blade angles and airspeeds. Results regarding the effect of icing and constant-power propeller operation are provided