Wind Tunnel Tests of a 5% A3J-1 Horizontal Ramp Inlet Model at Mach Numbers from Transonic to 2.25 PDF Download
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Author: Marion R. Bottorff
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 164
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Book Description
Author: Marion R. Bottorff
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 164
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Book Description
Author: Marion R. Bottorff
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 152
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Book Description
Author: Marion R. Bottorff
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 66
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Book Description
Author: Marion R. Bottorff
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 66
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Book Description
Author: Frederick K. Hube
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 278
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Book Description
Author: B. H. Goethert
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 424
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Book Description
Author: D. C. Baker
Publisher:
ISBN:
Category :
Languages : en
Pages : 61
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Book Description
A 1/9-scale model of the AMSA was tested in the Propulsion Wind Tunnel, Transonic (16T) and Propulsion Wind Tunnel, Supersonic (16S) of the Propulsion Wind Tunnel Facility (PWT). The test vehicle consisted of an airplane model and two pressure-instrumented inlet nacelles. Airplane model variations representing three-engine and four-engine configurations were tested with the two engine nacelles representing either two-thirds or one-half of the full airplane configuration. The three-engine configuration consisted of one pylon-mounted nacelle under the left wing and one tail-mounted nacelle above the fuselage on the airplane vertical centerline. The symmetrical four-engine configurations had either two adjacent nacelles suspended under the left wing or one forward nacelle under the left wing and one nacelle mounted aft on the left side of the fuselage near the tail. Data were obtained at free-stream Mach numbers from 0.60 to 2.30 to determine the performance characteristics of the inlets, and the effects of mutual interactions of inlets and airplane surfaces. The model attitude was varied throughout an angle-of-attack range of -4 to +11 deg and yaw angles of plus or minus 4 deg.
Author: James A. Behal
Publisher:
ISBN:
Category : Buffeting (Aerodynamics)
Languages : en
Pages : 692
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Book Description
A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
A 1/9-scale model of the AMSA was tested in the Propulsion Wind Tunnel, Transonic (16T) and Propulsion Wind Tunnel, Supersonic (16S) of the Propulsion Wind Tunnel Facility (PWT). The test vehicle consisted of an airplane model and two pressure-instrumented inlet nacelles. Airplane model variations representing three-engine and four-engine configurations were tested with the two engine nacelles representing either two-thirds or one-half of the full airplane configuration. The three-engine configuration consisted of one pylon-mounted nacelle under the left wing and one tail-mounted nacelle above the fuselage on the airplane vertical centerline. The symmetrical four-engine configurations had either two adjacent nacelles suspended under the left wing or one forward nacelle under the left wing and one nacelle mounted aft on the left side of the fuselage near the tail. Data were obtained at free-stream Mach numbers from 0.60 to 2.30 to determine the performance characteristics of the inlets, and the effects of mutual interactions of inlets and airplane surfaces. The model attitude was varied throughout an angle-of-attack range of -4 to +11 deg and yaw angles of plus or minus 4 deg.
Author: Neil Arthur Zarin
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 106
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Book Description
