Oscillating Pressures Near a Static Pusher Propeller at Tip Mach Numbers Up to 1.20 with Special Reference to the Effects of the Presence of the Wing PDF Download
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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: 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: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1338
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
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Book Description
Author: Royal Aeronautical Society
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 938
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 910
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Book Description
Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 308
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Book Description
Author: Harvey H. Hubbard
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 72
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Book Description
An analysis is presented whereby the free-space oscillating pressures associated with a rotating propeller may be determined at any point in space. This analysis is based on the fundamental Gutin equations without some of the simplifying assumptions. Static tests for several different propellers were conducted in the tip Mach number rang 0.45 to 1.00. Charts are given for estimating free-space pressures for a given propeller. The response of the fuselage to these oscillating pressures is also treated and some factors to be considered in solving the problems of fuselage vibration and noise are indicated.
Author: Max C. Kurbjun
Publisher:
ISBN:
Category : Propellers, Aerial
Languages : en
Pages : 20
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Book Description
In order to obtain information on the effects of blade plan form on the near-field noise of propellers, a series of measurements have been made of the oscillating pressures near a tapered-blade-plan-form propeller at flight Mach numbers up to 0.72. Flight Mach number, power, and engine speed were controlled in an attempt to duplicate the conditions of the flight investigation reported in NACA Technical Note 3417, where oscillating pressures were measured near a rectangular-blade-plan-form propeller.
Author: Arthur W. Vogeley
Publisher:
ISBN:
Category : Pressure
Languages : en
Pages : 24
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Book Description
(b) The sound-pressure levels of the higher harmonics of the propeller noise increase at a higher rate with increase in flight Mach number than the lower propeller harmonics.
Author: Harvey H. Hubbard
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Sound-pressure measurements are reported for five shrouded propellers and are compared with those for an unshrouded propeller operating at approximately the same rotational speed and power. The maximum total sound pressure produced by a two-blade shrouded propeller is found to vary approximately from one-half to twice as much as that for an unshrouded two-blade propeller, depending on whether the flow at the shroud surface is unseparated or separated, respectively. Shroud chord is found not to be critical except insofar as the areodynamic considerations are affected. In general, if the shroud-propeller unit satisfies aerodynamic requirements, good sound characteristics will also be obtained.
