| タイトル | Reynolds number influences in aeronautics |
| 本文（外部サイト） | http://hdl.handle.net/2060/19930022543 |
| 著者（英） | Yip, Long P.; Domack, Christopher S.; Hardin, Jay C.; Horvath, Thomas J.; Bushnell, Dennis M.; Lawing, Pierce L.; Fenbert, James W.; Yao, Chung-Sheng; Lin, John C.; Batina, John T. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1993-05-01 |
| 言語 | eng |
| 内容記述 | Reynolds number, a measure of the ratio of inertia to viscous forces, is a fundamental similarity parameter for fluid flows and therefore, would be expected to have a major influence in aerodynamics and aeronautics. Reynolds number influences are generally large, but monatomic, for attached laminar (continuum) flow; however, laminar flows are easily separated, inducing even stronger, non-monatomic, Reynolds number sensitivities. Probably the strongest Reynolds number influences occur in connection with transitional flow behavior. Transition can take place over a tremendous Reynolds number range, from the order of 20 x 10(exp 3) for 2-D free shear layers up to the order of 100 x 10(exp 6) for hypersonic boundary layers. This variability in transition behavior is especially important for complex configurations where various vehicle and flow field elements can undergo transition at various Reynolds numbers, causing often surprising changes in aerodynamics characteristics over wide ranges in Reynolds number. This is further compounded by the vast parameterization associated with transition, in that any parameter which influences mean viscous flow development (e.g., pressure gradient, flow curvature, wall temperature, Mach number, sweep, roughness, flow chemistry, shock interactions, etc.), and incident disturbance fields (acoustics, vorticity, particulates, temperature spottiness, even electro static discharges) can alter transition locations to first order. The usual method of dealing with the transition problem is to trip the flow in the generally lower Reynolds number wind tunnel to simulate the flight turbulent behavior. However, this is not wholly satisfactory as it results in incorrectly scaled viscous region thicknesses and cannot be utilized at all for applications such as turbine blades and helicopter rotors, nacelles, leading edge and nose regions, and High Altitude Long Endurance and hypersonic airbreathers where the transitional flow is an innately critical portion of the problem. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 93N31732
NASA-TM-107730
NAS 1.15:107730 |
| 権利 | No Copyright |
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