by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, National Technical Information Service, distributor] in [Washington, DC], [Springfield, Va .
Written in English
|Other titles||Slotted wall flow field measurements ....|
|Statement||Joel L. Everhart, William B. Igoe, and Stuart G. Flechner.|
|Series||NASA technical memorandum -- 4280.|
|Contributions||Igoe, William B., Flechner, Stuart G., United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.|
|The Physical Object|
Chapter 4. The Transonic Wind Tunnel and the NACA Technical Culture. by Steven T. Corneliussen. When nuclear physics emerged as a compelling field of fundamental scientific inquiry during the s, it needed new research tools, especially the invention of accelerators for probing nuclei with artificially energized subatomic particles. 1 Similarly, when the United . The flowfield on a segmented multi-slotted wind tunnel wall has been studied at transonic speeds by measurements in and near the wall layer using five port cone probes. The slotted wall ftowfield was observed to be three-dimensional in nature for a relatively significant distance above the slot. The boundary layer characteristics measured on theFile Size: 2MB. studied in wind-tunnel tests and free-flight experiments. iit trmsonic speeds less information is available, one reason for this being the ;?rexence of tunnel interference effects at stream Mach numbers near unity, wnich distort the flow field around the model. The Foot Transonic Tunnel (16’TT) contributions to the F Eagle program started in with tests on the Republic F proposal configuration and supplying a member (Bobby Berrier) to the F contract Source Evaluation Board. Multiple wind tunnel tests on the winning McDonnell Douglas configuration were conducted during to Center: Langley Research Center.
The Volvo Cars aerodynamic wind tunnel has had a vortical flow angularity pattern in the test section since its original commissioning in The vortical flow nature persisted after an upgrade in , when the fan was replaced and a moving ground system was introduced. It has been hypothesized that the cause for this flow angularity pattern was leakages around the Author: Emil Ljungskog, Simone Sebben, Alexander Broniewicz. wall pressure measurement systems that provide wall boundary measurements for the assessment of wind tunnel wall interference corrections. The systems were implemented in the Ames 12ft Pressure Wind Tunnel and the Ames 11ft Transonic Wind Tunnel.  Ulbrich, N. and Boone, A. R., “Direct Validation of the Wall InterferenceFile Size: 87KB. Design basis for a new transonic wind tunnel / J.B. Willis and N. Pollock; Experimental investigation into the use of a second throat in a continuous flow transonic wind tunnel / Slotted-wall flow-field measurements in a transonic wind tunnel [microform] / Joel L. Everhart, William. These tools included (1) the tunnel balance, which had been used by wind tunnel researchers for years as the standard means of measuring the aerodynamic forces on a model (i.e., lift, drag, and pitching moments); (2) orifices sensitive to pressures at various points on the surface of a model from whose measurements one could calculate local.
Wall corrections are derived for a major industrial wind tunnel (ONERA S2MA wind tunnel located in Modane). The tunnel is a transonic pressurised . On status of wind tunnel wall correction. the wind tunnel measurements of the high-lift semispan model were also corrected for wall Transonic flow Author: Bosko Rasuo. Slotted-wall flow-field measurements in a transonic wind tunnel [microform] / Joel L. Everhart, William Adaptive wall wind tunnels [microform]: a selected, annotated bibliography / Marie H. Tuttle, Elizabith Wall-interference assessment in three-dimensional slotted-wall wind tunnels [microform]: final technica. WIND TUNNEL WALL INTERFERENCE CORRECTIONS (A BRIEF OVERVIEW) BY N. Ulbrich Jacobs Technology Inc., Moffett Field, California June INTRODUCTION In general, an accurate description of wind tunnel test data (e.g., aerodynamic loads) and of important flow field phenomena (e.g., shock location, wing stall characteristics, etc.),File Size: 71KB.