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Computational Fluid Dynamics Testing for Drag Reduction of an Aircraft Laser Turret | 
 enlarge | Publisher: Storming Media
Category: Book
Buy New: $33.95
Media: Spiral-bound
Pages: 114
ISBN: 1423536282
EAN: 9781423536284
ASIN: 1423536282
Publication Date: 2000
Availability: Usually ships in 1-2 business days
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Condition: Please note that this is a report or document and is not a book, per se. It is 114 pages long and is Velobound in a soft linen cover. This technical report was sponsored by the Pentagon and is provided in the best form available to the government. Sometimes our report quality is picture perfect and in color; other times, particularly for older reports, extensive black-and-white photocopying has degraded the quality. If you have any questions about quality of a particular report, please ask and we would be happy to describe it in more detail.
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Product Description
This is a AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING report procured by the Pentagon and made available for public release. It has been reproduced in the best form available to the Pentagon. It is not spiral-bound, but rather assembled with Velobinding in a soft, white linen cover. The Storming Media report number is A592083. The abstract provided by the Pentagon follows: A computational study was conducted on the use of aft-mounted fairings for passive drag reduction on a sphere at Re=866,000. The sphere dimensions and operating Reynolds number were selected to approximate the flow around a proposed aircraft laser turret for which experimental data was available. To establish the validity of the computational model, flow predictions were compared to sphere data available in the open literature. The model, exercised in both the laminar and turbulent modes, showed good agreement with the published data. Two proposed laser turret fairings were then evaluated computationally: a large fairing (beginning at 49.5 degrees past the sphere apex) and a small fairing (beginning at 58.95 degrees past the sphere apex). Existing wind tunnel models were used to generate axisymmetric computational grids that approximated the geometry of these models. The computed flow field and associated drag reduction were comparable to the experimental results obtained from the wind tunnel testing. Differences in drag from the model to the experiment were explained by the axisymmetric simplifications made in the model. Finally, a new, optimized fairing model was designed which eliminated the separation zone on the aft portion of the sphere. The optimized model predicted double the drag reduction compared to the large fairing computational model.
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