[PDF] Aerodynamic Loads On An Isolated Shrouded Propeller Configuration For Angles Of Attack From 10 Degrees To 110 Degrees eBook

Author : KALMAN J. GRUNWALD
Publisher :
Page : 1 pages
File Size : 21,24 MB
Release : 1962
Category :
ISBN :

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An investigation of the division of loads between the propeller and the shroud of a shroudedpropeller configuration was conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. This investigation covered an angle-of-attack range from -10 to 110 degrees and a range of advance ratios (0 to 0.595) typical of the transition speed range of a tilt-duct VTOL aircraft. For the configurations with fixed blade angle (24 degrees at the three-quarter radius), the normal force and pitching moment developed by the propeller and spinner were only a relatively small part of the over-all normal force and pitching moment of either a stalled or an unstalled shroud. The ratio of the thrust of the propeller and spinner to total thrust was found to vary from about 0.4 in hovering to about 0.7 at the highest advance ratio of the tests, 0.595, with the shroud at zero angle of attack. (Author).

Author : Dietrich Knoerzer
Publisher : Springer Nature
Page : 290 pages
File Size : 35,54 MB
Release : 2022-12-12
Category : Technology & Engineering
ISBN : 3031120191

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This book provides research results using computational methods for fluid dynamics and engineering problems in aeronautics and other scientific and industrial applications. It gives an overview on the state of the art and the technology trends requiring advanced computational methods towards digitization in industrial and scientific processes. The chapters are based on Special Technology Sessions of the WCCM-ECCOMAS Virtual Congress 2021.

Author : JOHN P. JR. MUGLER
Publisher :
Page : 1 pages
File Size : 38,83 MB
Release : 1961
Category :
ISBN :

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The static longitudinal aerodynamic characteristics of a blunted right triangular pyramidal lifting reentry configuration have been obtainedAT Mach numbers from 0.60 to 1.20 and angles of attack from 0 degrees to 110 degrees. The test Reynolds number, based on the mean geometric chord, varied during the tests from about 2.2 x 10 to the 6th power to 5.7 x 10 to the 6th power. The results indicate that the model was statically longitudinally stable near 0 degrees and 90 degrees angle of attack; however, the onset of pitch-up caused unstable or neutrally stable regions between angles of attack of about 25 degrees to 50 degrees. Maximum lift-drag ratios of about 2.4 were obtained at subsonic speeds and then diminished to about 1.6 at low supersonic speeds. Comparisons with data from other tests indicate that blunting the nose, leading edge, and ridge line had little effect on the maximum lift-drag ratio. (Author).

Author : JACK F. RUNCKEL
Publisher :
Page : 1 pages
File Size : 45,41 MB
Release : 1961
Category :
ISBN :

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An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).