Numerical and Experimental Analysis of the Effect of a Pusher Propeller on a Wing and Body PDF Download
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Author: F. M. Catalano
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: F. M. Catalano
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Harvey H. Hubbard
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 46
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Book Description
Measurements of free-space oscillating presssures near a static propeller in the region where a wing might be located are presented for the tip Mach number range of 0.50 to 1.20 and these results are compared with available theory. Some measurements are also presented which were made near the tipes in the region where a fuselage might be located in order to extend the range of existing data from a tip Mach number of 1.00 to 1.20. In addition to a description of the free-space pressure field, meausrements are given from some of the same field points with a wing in place.
Author: International Council of the Aeronautical Sciences. Congress
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1408
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Author: Carl A. Sandahl
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 50
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Summary: Some of the effects of pusher-propeller operation on the aerodynamic characteristics of a flapped wing were measured in the Langley propeller-research tunnel. The effects of propeller operation on the lift and profile drag of the wing, on pressure distribution, and on the position of boundary-layer transition were obtained. The results indicated that, at fixed angles of attack and with flaps deflected, the wing lift increased appreciably with increasing thrust coefficient. With flaps retracted, no appreciable increase in lift with increases in thrust coefficient was measured. Chordwise pressure distributions at several spanwise stations indicated that the effect of propeller operation was greatest in the region immediately ahead of the propeller and that the effect extended out-board from the propeller axis for about 2.5 propeller radii. Measurements of boundary-layer velocity on the forward part of the upper surface of the wing showed no appreciable shift of transition in the range of thrust coefficients investigated.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 564
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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 622
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1338
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Author: John P. Campbell
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 56
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Summary: The effects on stability and control of a pusher propeller behind conventional horizontal and vertical tail surfaces have been determined in the NACA free-flight tunnel by tests of a 1/10-scale model of an NACA submerged-engine pusher airplane design. The investigation consisted of flight and balance tests at windmilling and high-power conditions with a partial-span Zap extensible flap extended and retracted. The effects of changes in vertical-tail area, horizontal-tail incidence, and center-of-gravity location were also determined.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 39
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An experimental investigation of the noise generated by a pusher propeller due to a wake entering the propeller disc was conducted. Acoustic measurements were made in a low speed wind tunnel with the propeller operating in a uniform velocity airstream, and with a wind mounted at various locations upstream of the propeller. For the propeller alone case the experimental results were compared with theoretical results.
