Experiments on the flow past a circular cylinder at very high Reynolds number

@article{Roshko1961ExperimentsOT,
  title={Experiments on the flow past a circular cylinder at very high Reynolds number},
  author={Anatol Roshko},
  journal={Journal of Fluid Mechanics},
  year={1961},
  volume={10},
  pages={345 - 356}
}
  • A. Roshko
  • Published 1 May 1961
  • Engineering, Physics
  • Journal of Fluid Mechanics
Measurements on a large circular cylinder in a pressurized wind tunnel at Reynolds numbers from 106 to 107 reveal a high Reynolds number transition in which the drag coefficient increases from its low supercritical value to a value 0.7 at R = 3.5 × 106 and then becomes constant. Also, for R > 3.5 × 106, definite vortex shedding occurs, with Strouhal number 0.27. 

On vortex shedding from a circular cylinder in the critical Reynolds number régime

The flow around a circular cylinder has been examined over the Reynolds number range 105 to 7·5 × 105, Reynolds number being based on cylinder diameter. Narrow-band vortex shedding has been observed

On the wake transition in the flow past a circular cylinder at critical Reynolds numbers

In this paper advanced turbulence simulations at Reynolds numbers in the range of 1.4× 10-8.5× 10 will be carried out by means of large-eddy simulations. Numerical simulations using unstructured

An experiment on the flow past a finite circular cylinder at high subcritical and supercritical Reynolds numbers

The complicated flow in the tip region of a finite circular cylinder in uniform cross flow has been examined at the Reynolds numbers 0·85 × 105, 1·8 × 105, and 7·7 × 105. Simultaneous measurements of

On the Drag Reduction of a Circular Cylinder at High Reynolds Numbers

The flow past a circular cylinder has been examined over the Reynolds number range 10 exp 4 to 6 x 10 exp 5 in the presence of a small control cylinder/airfoil placed immediately outside of the wake

Coherent Shedding from a Circular Cylinder at Critical, Supercritical, and Transcritical Reynolds Numbers

Results are summarized from NASA-Langley studies of the mean drag and unsteady flow parameters of the flow around a circular cylinder at critical, supercritical and transcritical Re. Flow velocities

Study of Viscous Crossflow Effects on Circular Cylinders at High Reynolds Numbers

Results of experimental studies on viscous cross-flow over circular cylinders for Reynolds numbers from 0.15 x 10 to the 6th to 10.9 x 10 to the 6th at Mach numbers of less than 0.3 are presented and

HIGH REYNOLDS NUMBER OSCILLATING FLOW BY CYLINDERS

In order to determine the added mass, drag and lift coefficients of a smooth cylinder at various distances from a plane boundary, the forced cylinder oscillation tests at high Reynolds number 105 to

Supercritical Reynolds number simulation for two-dimensional flow over circular cylinders

In wind-tunnel tests on bluff bodies the Reynolds number is often limited to values that are very much smaller than those of the flows being simulated. In such cases the experiments may have no
...

References

SHOWING 1-10 OF 22 REFERENCES

Fluctuating Lift and Drag Acting on a Cylinder in a Flow at Supercritical Reynolds Numbers

The fluctuating lift and drag acting on a circular cylinder in a flow of an incompressible fluid at large Reynolds numbers were measured. Data on the root-mean-square values of the lift and drag

Hot-wire investigation of the wake behind cylinders at low Reynolds numbers

  • L. Kovasznay
  • Physics
    Proceedings of the Royal Society of London. Series A. Mathematical and Physical Sciences
  • 1949
The hot-wire technique has been used to measure the regular vortex street pattern behind a cylinder at low Reynolds number. Measurements of mean velocity distribution were made both below and above

Low-speed drag of cylinders of various shapes

Report presenting an investigation to find the approximate variation of the drag coefficient with Reynolds number of several cylinders with different cross-sectional shapes. Data were obtained for

Wall interference in a two-dimensional-flow wind tunnel, with consideration of the effect of compressibility

Theoretical tunnel-wall corrections are derived for an airfoil of finite thickness and camber in a two-dimensional-flow wind tunnel. The theory takes account of the effects of the wake of the airfoil

Experimental investigation of localized regions of laminar-boundary-layer separation

Report presenting an investigation of the localized region of laminar separation behind the position of minimum pressure on an NACA 663-018 airfoil at zero angle of attack. A description of the

On the Wake and Drag of Bluff Bodies

A modification to Kirchhoff's free streamline introduces the parameter k = √(1- C_ps), which allows arbitrary base pressure and which must depend on the dynamics of the wake. For a cylinder of given

On the drag and shedding frequency of two-dimensional bluff bodies

Note presenting a semiempirical study of the bluff-body problem. Some experiments with interference elements in the wake close behind a cylinder demonstrate the need for considering that region in

Advanced Education and Academic Research in Aeronautics

  • C. B. Millikan
  • Geology
    The Journal of the Royal Aeronautical Society
  • 1957
The Forty-Fifth Wilbur Wright Memorial Lecture, “Advanced Education and Academic Research in Aeronautics” was given before the Society by Dr. Clark B. Millikan, Hon.F.I.A.S., F.R.Ae.S., on 13th

Neuere Feststellungen iiber die Gesetze des Fliissigkeits-und Luftwiderstands. Phys. 2

  • Neuere Feststellungen iiber die Gesetze des Fliissigkeits-und Luftwiderstands. Phys. 2
  • 1921