Analysis of wings using Airfoil NACA 4412 at different angle of attack

@inproceedings{Ijmer2014AnalysisOW,
  title={Analysis of wings using Airfoil NACA 4412 at different angle of attack},
  author={Journal Ijmer and Agrawal Mahendra and Saxena Gaurav},
  year={2014}
}
The purpose of this paper is to analysis the basic aerodynamic theory of wings and the provide an introduction to wind tunnel testing. This is followed by the result from the wind tunnel testing of a NACA4412 and the analysis of the data. Lift increase at the angle of attack increase at certain point and at this point it become maximum. After that if the angle of attack is increased by further, drag become the dominant factor and the wind enters the stall mode. 

Figures from this paper.

References

Publications referenced by this paper.
SHOWING 1-10 OF 14 REFERENCES

A flying hot-wire study of separated flows

O. O. Badran
  • Ph.D thesis. University of Bradford,
  • 1993

Evaluation of a flying x hot-wire probe system

Al-Kayiem H.H, Bruun H.H
  • Meas. Sci. Technol
  • 1991

Characteristics of the flow around conventional and supercritical airfoils

A. Nakayama
  • J. Fluid Mech
  • 1985

Studies of the flow field near an NACA 4412 aerofoil at nearly maximum lift

R. C. Hastings, B. R. William
  • Royal Aircraft Establishment,
  • 1984

Experimental Studies of the Eppler 61 airfoil at low Reynolds numbers

T. F. Burns, T. J. Mueller
  • AIAA 20th Aerospace Science Meeting,
  • 1982