Calibration of the AEDC-PWT 16-ft Transonic Tunnel with the Propulsion Test Section at Various Reynolds Numbers PDF Download
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Author: F. M. Jackson Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 104
Book Description
Tests were conducted in the AEDC Propulsion Wind Tunnel (16T) to determine the tunnel test section Mach number distributions and calibration at various Reynolds numbers. The calibration was conducted at Mach numbers from 0.2 to 1.6 and at Reynolds numbers from 400,000/ft to 6,400,000/ft. The calibration was conducted using the propulsion test section (Test Section 1) and centerline pipe and wall pressure orifices to define the Mach number distributions. A quantitative evaluation of the effects of tunnel pressure ratio, test section wall angle, and Reynolds number on the centerline Mach number distributions was determined by analysis of the local Mach number deviations. The results indicate that Mach number distributions of good quality are obtained for both zero and the optimum wall angle schedule. For complete generality, the Tunnel 16T calibration must be defined as a function of test section wall angle, Reynolds number, and Mach number.
Author: F. M. Jackson Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 104
Book Description
Tests were conducted in the AEDC Propulsion Wind Tunnel (16T) to determine the tunnel test section Mach number distributions and calibration at various Reynolds numbers. The calibration was conducted at Mach numbers from 0.2 to 1.6 and at Reynolds numbers from 400,000/ft to 6,400,000/ft. The calibration was conducted using the propulsion test section (Test Section 1) and centerline pipe and wall pressure orifices to define the Mach number distributions. A quantitative evaluation of the effects of tunnel pressure ratio, test section wall angle, and Reynolds number on the centerline Mach number distributions was determined by analysis of the local Mach number deviations. The results indicate that Mach number distributions of good quality are obtained for both zero and the optimum wall angle schedule. For complete generality, the Tunnel 16T calibration must be defined as a function of test section wall angle, Reynolds number, and Mach number.
Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
Tests were conducted in the AEDC Propulsion Wind Tunnel (16T) to determine the tunnel test section Mach number distributions and calibration at various Reynolds numbers. The calibration was conducted at Mach numbers from 0.2 to 1.6 and at Reynolds numbers from 400,000/ft to 6,400,000/ft. The calibration was conducted using the propulsion test section (Test Section 1) and centerline pipe and wall pressure orifices to define the Mach number distributions. A quantitative evaluation of the effects of tunnel pressure ratio, test section wall angle, and Reynolds number on the centerline Mach number distributions was determined by analysis of the local Mach number deviations. The results indicate that Mach number distributions of good quality are obtained for both zero and the optimum wall angle schedule. For complete generality, the Tunnel 16T calibration must be defined as a function of test section wall angle, Reynolds number, and Mach number.
Author: F. M. Jackson Publisher: ISBN: Category : Transonic wind tunnels Languages : en Pages : 182
Book Description
Tests were conducted in the AEDC Propulsion Wind Tunnel (16T) to determine the tunnel test section Mach number distributions and calibration at various Reynolds numbers. Two separate test entries were made. Collectively, the calibration was conducted at Mach numbers from 0.2 to 1.6 and at Reynolds numbers from 500,000/ft to 6 million/ft. The calibration was conducted with the aerodynamic test section (Test Section 2) using a centerline pipe and/or wall pressure orifices to define the Mach number distributions. A quantitative evaluation of the effects of tunnel pressure ratio, test section wall angle, and Reynolds number on the tunnel Mach number distributions and calibration was accomplished. Results indicate that good quality Mach number distributions are obtained for both zero and the optimum wall angle schedule. To obtain the maximum accuracy, the Tunnel 16T calibration must be defined as a function of test section wall angle, Reynolds number, and Mach number. Comparison of this calibration with previous calibration results indicates that a revision in the tunnel calibration used for operations is desirable. Analytical expressions which represent the tunnel calibration at various test conditions were developed for use during Tunnel 16T operations.
Author: F. M Jackson (III.) Publisher: ISBN: Category : Languages : en Pages : 179
Book Description
Tests were conducted in the AEDC Propulsion Wind Tunnel (16T) to determine the tunnel test section Mach number distributions and calibration at various Reynolds numbers. Two separate test entries were made. Collectively, the calibration was conducted at Mach numbers from 0.2 to 1.6 and at Reynolds numbers from 500,000/ft to 6 million/ft. The calibration was conducted with the aerodynamic test section (Test Section 2) using a centerline pipe and/or wall pressure orifices to define the Mach number distributions. A quantitative evaluation of the effects of tunnel pressure ratio, test section wall angle, and Reynolds number on the tunnel Mach number distributions and calibration was accomplished. Results indicate that good quality Mach number distributions are obtained for both zero and the optimum wall angle schedule. To obtain the maximum accuracy, the Tunnel 16T calibration must be defined as a function of test section wall angle, Reynolds number, and Mach number. Comparison of this calibration with previous calibration results indicates that a revision in the tunnel calibration used for operations is desirable. Analytical expressions which represent the tunnel calibration at various test conditions were developed for use during Tunnel 16T operations.
Author: F. M. Jackson Publisher: ISBN: Category : Languages : en Pages : 169
Book Description
Tests were conducted in the AEDC Propulsion Wind Tunnel (16T) to determine the centerline Mach number distributions and the tunnel calibration at test section wall porosities of two, four, and six percent. The calibration was conducted over the Mach number range from 0.2 to 1.6. A quantitative evaluation of the effects of Mach number, tunnel pressure ratio, test section wall angle, and test section wall porosity upon the centerline Mach number distributions was determined by analysis of the local Mach number deviations. Limited data were also obtained to provide an indication of the effect of Reynolds number upon the calibration. The results indicate that Mach number distributions of good flow quality are obtained at porosities of two, four, and six percent for test section wall angles which vary from 0 to 0.50 deg. Variation of test section wall porosity, as well as wall angle, significantly affects the Tunnel 16T calibration. Comparison of this calibration with a previous calibration, however, indicates that no new tunnel calibration is required for operation at a porosity of six percent with either a zero or optimum wall angle schedule. (Author).
Author: G. D. Robson Publisher: ISBN: Category : Languages : en Pages : 34
Book Description
Tests were conducted in the Propulsion Wind Tunnel, Transonic (16T) of the Propulsion Wind Tunnel Facility to determine the test section temperature distribution and calibration relationship to a mean nozzle reference temperature while using a cryogenic cooling system to produce stagnation temperatures from -30 to 30F. Data were obtained over the Mach number range 0.20
Author: J. A. GUNN Publisher: ISBN: Category : Languages : en Pages : 55
Book Description
Tests were conducted in the Propulsion Wind Tunnel, Transonic (16T) of the Propulsion Wind Tunnel Facility to determine the test section Mach number calibration and Mach number distributions. During the test, Mach number was varied from 0.50 to 1.60, and the wall angle from -1.00 to +1.00 deg, while holding tunnel total pressure at 1000 psfa and tunnel temperature at 120F. At all Mach numbers the region from Station 1 to Station 20 was considered the test region. The results show that the tunnel calibration is a function of test section wall angle, and that all wall angles in the calibrated Mach number range produce Mach number distributions acceptable for testing. This was the first calibration after the installation of the modified main compressor utilizing fiber glass rotor blades. (Author).
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Propulsion and Energetics Panel Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 404
Author: F. M. Jackson
Author: F. M. Jackson
Author: 
Author: F. M. Jackson
Author: F. M Jackson (III.)
Author: F. M. Jackson
Author: 
Author: G. D. Robson
Author: J. A. GUNN
Author: 
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Propulsion and Energetics Panel