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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725058200
Category :
Languages : en
Pages : 26
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Book Description
A wall signature method has been selected to be adapted for the Ames 12-ft Wind Tunnel WIAC system. This uses limited measurements of the static pressure at the wall, in conjunction with the solid wall boundary condition, to determine the strength and distribution of singularities representing the test article. The singularities are used to estimate wall interference at the model location. The development and implementation of a working prototype will be completed, delivered and documented with a software manual. Lo, C. F. Unspecified Center NASA-CR-196940, NAS 1.26:196940 NAG2-733...
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725058200
Category :
Languages : en
Pages : 26
Get Book Here
Book Description
A wall signature method has been selected to be adapted for the Ames 12-ft Wind Tunnel WIAC system. This uses limited measurements of the static pressure at the wall, in conjunction with the solid wall boundary condition, to determine the strength and distribution of singularities representing the test article. The singularities are used to estimate wall interference at the model location. The development and implementation of a working prototype will be completed, delivered and documented with a software manual. Lo, C. F. Unspecified Center NASA-CR-196940, NAS 1.26:196940 NAG2-733...
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725058330
Category :
Languages : en
Pages : 38
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Book Description
A Wall Signature method originally developed by Hackett has been selected to be adapted for the Ames 12-ft Wind Tunnel WIAC system in the project. This method uses limited measurements of the static pressure at the wall, in conjunction with the solid wall boundary condition, to determine the strength and distribution of singularities representing the test article. The singularities are used in turn for estimating blockage wall interference. The lifting interference will be treated separately by representing in a horseshoe vortex system for the model's lifting effects. The development and implementation of a working prototype will be completed, delivered and documented with a software manual. The WIAC code will be validated by conducting numerically simulated experiments rather than actual wind tunnel experiments. The simulations will be used to generate both free-air and confined wind-tunnel flow fields for each of the test articles over a range of test configurations. Specifically, the pressure signature at the test section wall will be computed for the tunnel case to provide the simulated 'measured' data. These data will serve as the input for the WIAC method--Wall Signature method. The performance of the WIAC method then may be evaluated by comparing the corrected data with those of the free-air simulation. Lo, Ching F. and Overby, Glenn and Qian, Cathy X. and Sickles, W. L. and Ulbrich, N. Unspecified Center NASA-CR-191889, NAS 1.26:191889 NAG2-733...
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722040581
Category :
Languages : en
Pages : 44
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Book Description
Development of complex air vehicle configurations is placing increasing demands on wind tunnel testing capabilities. A major area of concern is wall induced interference. Recent developments in wall interference technology provide a means for assessing and correcting for the wall induced interference using information contained in the distribution of flow variables measured at, or near, the wall. The restoration of the NASA-ARC 12-ft pressure wind tunnel (PWT) provides an opportunity to incorporate a measurement system with which wall interference assessment/correction (WIAC) technology can be applied. In this first phase of the development of a WIAC system for the PWT, the design criteria for the placement and the geometry of wall static pressure orifices were determined with a three step approach. First, the operational environment of the PWT was analyzed as to the requirements for the WIAC system. Second, appropriate wall interference theories were evaluated against the requirements determined from the operational environment. Third, the flow about representative models in the PWT was calculated and, specifically, the pressure signatures at the location of the test section wall were obtained. The number of discrete pressure measurements and their locations were determined by curve fitting the pressure distribution through the discrete measurements and evaluating the resulting error. Unspecified Center NAG2-551...
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: W. L. Sickles
Publisher:
ISBN:
Category :
Languages : en
Pages : 108
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Book Description
Evaluation of wall interference correction procedures was performed using experimental data. The correction procedures incorporated the use of measured data made on an interface near the tunnel wall and the use of two flow-field solvers, a transonic small disturbance solver and an Euler solver. Interference corrections were calculated for data obtained in Tunnel 1T with varying amounts of interference. Results are given for representative subcritical, mildly supercritical, and supercritical flows. Calculated interference levels are compared to experimental interference levels between the interference-free reference data from Tunnel 4T and the data with interference from Tunnel 1T. Keywords: Wall interference; Transonic testing; Wind tunnel data; Flight performance prediction; Assessment techniques; Correction techniques. (JHD).
Author: Clyde Robert Gumbert
Publisher:
ISBN:
Category :
Languages : en
Pages : 120
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Author: Perry A. Newman
Publisher:
ISBN:
Category : Wind tunnel walls
Languages : en
Pages : 440
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781729323144
Category :
Languages : en
Pages : 60
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Book Description
A wind-tunnel interference assessment method applicable to test sections with discrete finite-length wall slots is described. The method is based on high order panel method technology and uses mixed boundary conditions to satisfy both the tunnel geometry and wall pressure distributions measured in the slotted-wall region. Both the test model and its sting support system are represented by distributed singularities. The method yields interference corrections to the model test data as well as surveys through the interference field at arbitrary locations. These results include the equivalent of tunnel Mach calibration, longitudinal pressure gradient, tunnel flow angularity, wall interference, and an inviscid form of sting interference. Alternative results which omit the direct contribution of the sting are also produced. The method was applied to the National Transonic Facility at NASA Langley Research Center for both tunnel calibration tests and tests of two models of subsonic transport configurations. Kemp, William B., Jr. Unspecified Center...
Author: Eric Lee Walker
Publisher:
ISBN:
Category :
Languages : en
Pages : 270
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Book Description
