Titlebook: New Results in Numerical and Experimental Fluid Mechanics; Contributions to the Horst K?rner,Reinhard Hilbig Book 1997 Friedr. Vieweg & Soh

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書目名稱New Results in Numerical and Experimental Fluid Mechanics影響因子(影響力)




書目名稱New Results in Numerical and Experimental Fluid Mechanics影響因子(影響力)學(xué)科排名




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書目名稱New Results in Numerical and Experimental Fluid Mechanics網(wǎng)絡(luò)公開度學(xué)科排名




書目名稱New Results in Numerical and Experimental Fluid Mechanics被引頻次




書目名稱New Results in Numerical and Experimental Fluid Mechanics被引頻次學(xué)科排名




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書目名稱New Results in Numerical and Experimental Fluid Mechanics年度引用學(xué)科排名




書目名稱New Results in Numerical and Experimental Fluid Mechanics讀者反饋




書目名稱New Results in Numerical and Experimental Fluid Mechanics讀者反饋學(xué)科排名

Climate

Density Measurements on a Delta Wing by Means of Planar Intensity Distribution of Rayleigh Scatteredences made during these first tests, the quantitative determination of the density field above a delta wing has been performed at Mach numbers between 0.5 and 1.4 in the transonic wind tunnel (TWG) of the DLR G?ttingen. Three dimensional density fields with a resolution of about 1% have been obtained.

Deceit

Numerical and Experimental Investigations of Flow Induced by Harmonic Motion of a Circular Cylindernder in water at rest at Reynolds number Re=100 and Keulegan-Carpenter number KC=5 was computed accurately in time. Computations have been performed applying different grid levels and time steps. Stable, symmetric and periodic flow patterns occurred showing good agreement with time averaged LDA measurements providing phase resolution of 1 degree.

anaerobic

Alternative drag calculations from off body flow quantities using the FLOWer codeentional surface force integration techniques. The method is applied to two-dimensional flow field solutions obtained from the FLOWer code. Qualitative comparisons of the two techniques are presented for a NACA 0012 airfoil at different Mach numbers.

種植,培養(yǎng)

Commentary

變化

bifurcate

contrast-medium

nonchalance

Reduction of Aerodynamic Drag (RaWid) in the national Research and Technology Programme for Aeronautlogies required for a MEGALINER which gains momentum by the ambitious plans for a new large Airbus A3XX..In the first year new technological steps were undertaken in theory, design and experiment. Some critical steps were verified by wing designs checked in wind tunnel tests.