Abstract
A method is described for rapidly measuring and visualizing the extent of separated flow suitable for a wind tunnel environment. The method utilizes a continuously swinging total pressure probe. This technique permits acquiring and presenting graphical records of separated regions in a fraction of the time required by other methods. Typical results indicate the presence of highly complicated three-dimensional separated regions for a typical general aviation twin-engine aircraft at post-stall conditions.
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Abbreviations
- c:
-
wing mean geometric chord
- cpt :
-
total pressure coefficient, (P T-PS)/q ∞
- P S :
-
static pressure
- P T :
-
total pressure
- q∞:
-
free stream dynamic pressure
- q :
-
local dynamic pressure
- r :
-
radial direction
- x :
-
streamwise coordinate (x=0 corresponds to leading edge of wing)
- α:
-
angle of attach
- ϕ:
-
azimuth direction
References
Crowder, J. P. 1980: Quick and easy flow-field surveys. Aeronautics Astronautics, 38–45
Kiel, G. 1935: A total-head meter with small sensitivity to yaw. NACA TM 775
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Ostowari, C. A rapid technique for measuring and visualizing the extent of separated flow. Experiments in Fluids 2, 67–72 (1984). https://doi.org/10.1007/BF00261324
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DOI: https://doi.org/10.1007/BF00261324