By Joslin, Ronald D.; Jones, Gregory S.(eds.)
In keeping with papers from the 2004 NASA/ONR movement keep watch over Workshop, this assortment is a useful, distinctive source at the state of the art in stream keep an eye on applied sciences and purposes. Filling the knowledge hole among 1986, whilst the final such symposium was once held, and at the present time, it summarizes the purposes, experiments, computations and theories on the topic of stream regulate, emphasizing primary physics, platforms research and utilized study. The papers offered hide a wide selection of aerodynamic and hydrodynamic functions together with; naval cars, fixed-wing aviation, V/STOL structures, propulsion platforms, and flooring vehicles.
- information and data showing during this booklet are for informational reasons in basic terms. AIAA and the writer should not accountable for any harm or harm due to use or reliance, nor do AIAA and the writer warrant that use or reliance should be unfastened from privately owned rights.
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Additional info for Applications of Circulation Control Technologies
026 in. 032 in. 040 in. \ INVESTIGATIONS OF CC TECHNOLOGY AT NSWCCD 87 Surface Pressure Taps Centerline Cross-section Fig. '* blowing coefficient C,. The optimum, or highest lift, configuration varied somewhat with the C, level. The overall highest lift was obtained using a 225-deg perimeter of fluid ejection centered about the trailing edge. It is notable that high lift performance was obtained even with full perimeter blowing, showing that the omnidirectional configuration is viable. Figure 24 reveals lift performance results for the 225-deg perimeter configuration at several AOA and C, levels.
Here, a short-chord flap (less than 0 . 1 0 ~ pivots ) about a hinge on the lower surface and exposes a smaller-radius CCW surface downstream of the tangential slot. This radius is approximately the airfoil thickness at the slot location, less the slot height. The upper surface of this flap is a second arc of much larger radius, the radius being chosen to keep the arc close to the airfoil aft contour. As the small flap is deflected on this dual-radius CCW airfoil, the large radius produces an arced CC aft surface with a turning arc much larger than the flap deflection angle.
25 implies the potential for high lift and drag for STOL approach (remember, induced drag due to high lift is not included in this data for two-dimensional airfoils) or high lift and reduced drag for takeoff. Figure 26 shows the capability of this nonmoving LE device to reattach flow, prevent stall, and dramatically increase C , . Figure 27 combines the above data in terms of Cl vs LID,, where the equivalent drag coefficient is defined as CDE= Cd C, to account for the blowing required to yield these drag changes.