12 research outputs found
Aerodynamic Characteristics at High Speeds of Related Full-Scale Propellers Having Different Blade-Section Cambers
Wind-tunnel tests of a full-scale two-blade NACA 10-(10)(08)-03 (high camber) propeller have been made 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 have been compared with results from previous tests of the NACA 10-(3) (08)-03 (low camber) and NACA 10-(5)(08)-03 (medium camber) propellers to evaluate the effects of blade-section camber on propeller aerodynamic characteristics
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NACA Research Memorandums
Memorandum presenting total-pressure surveys made in the slipstreams of two full-scale three-blade supersonic propellers in the 16-foot transonic tunnel at Mach numbers up to 1.04 to determine the effects of camber on supersonic-propeller characteristics. The two propellers were similar except that one of them had symmetrical blade sections and the other had cambered blade sections and a slightly different pitch distribution. Over the complete range of the tests, the cambered propeller maintained higher thrust and efficiency
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NACA Research Memorandums
Report presenting an investigation of NACA 8.75-(5)(05)-037 eight- and six-blade dual-rotating propellers under static conditions. The slipstream-boundary cone angle was found to agree with the theoretical angle of spread for an unheated jet. Results regarding the longitudinal survey, stationary survey, effect of blade angle, nature of flow near propeller, and effect of blade angle on slipstream rotation are provided
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NACA Technical Reports
From Summary: "Wind-tunnel tests of a full-scale two-blade NACA 10-(10)(08)-03 (high camber) propeller have been made 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 have been compared with results from previous tests of the NACA 10-(3) (08)-03 (low camber) and NACA 10-(5)(08)-03 (medium camber) propellers to evaluate the effects of blade-section camber on propeller aerodynamic characteristics.
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NACA Research Memorandums
From Introduction: "This paper presents the test data obtained for the NACA 10-(3) (08)-03R propeller blade which was one of the blades tested to determine the effects of shank design.
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NACA Research Memorandums
"An investigation has been conducted at the Langley 16-foot transonic tunnel at Mach number of about 0.14 (110 miles per hour) to determine the aerodynamic loading on a three-blade, 9.75-foot-diameter, supersonic-type propeller when used as a brake. The results of the slipstream survey are presented without analysis in tabular form for blade-angle settings at the 0.75 radial station from 16.4 degrees to -13.6 degrees in approximately 5 degree increments" (p. 1)