Calibration of the AEDC-PWT 16-ft Transonic Tunnel at Test Section Wall Porosities of Two, Four, and Six Percent PDF Download
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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: 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: 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 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 (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: O. P. Credle Publisher: ISBN: Category : Transonic wind tunnels Languages : en Pages : 78
Book Description
The report presents the results of recent studies of noise in Propulsion Wind Tunnel (16T) and Aerodynamic Wind Tunnel (4T). Noise levels in the free stream and at the test section wall were measured in both tunnels as a function of Mach number, Reynolds number, wall angle, and wall porosity. In Tunnel 4T, free-stream noise characteristics were also evaluated with solid (taped) test section walls. Test results revealed that the perforated test section wall holes generate discrete frequency, high energy noise. In Tunnel 16T, there is a critical Mach number range in which a wall hole frequency. Test section noise levels were found to vary slightly with wall angle and significantly with Mach number and wall porosity. The wall porosity corresponding to the minimum noise levels was found in Tunnel 4T. (Author).
Author: S. Hartley Publisher: ISBN: Category : Languages : en Pages : 57
Book Description
Tests were conducted in the AEDC Aerodynamic Wind Tunnel, Transonic (4T), to determine the tunnel calibration, Mach number distributions, and boundary-layer thicknesses. During the tests, Mach number was varied from 0.1 to 1.4, test section wall angle from -0.5 to 0.5 deg, and test section wall porosity from 0 to 10 percent. Data were obtained at various stagnation pressure levels from 500 to 2500 psf. Considerable development of the flow expansion region was required to obtain uniform supersonic Mach number distributions. Good Mach number distributions are obtainable up to and including Mach number 1.2. The distributions from Mach number 1.25 to 1.4 are suitable only for very limited testing. The results show that the tunnel calibration is a function of test section wall porosity and wall angle. Boundary-layer thicknesses on the contoured walls and parallel walls at the nozzle exit are nearly equal. (Author).
Author: F. M. Jackson
Author: F. M. Jackson
Author: F. M. Jackson
Author: F. M. Jackson
Author: 
Author: F. M Jackson (III.)
Author: O. P. Credle
Author: 
Author: T. D. Reed
Author: 
Author: S. Hartley