Abstract
The effect of Reynolds number on the geometric characteristics of flow under conditions of boundary layer separation from the surface of a sphere is analyzed.
The point of boundary layer separation is determined.
The angle between the tangent to the surface of the sphere at the point of its intersection with the extension of the shock wave and the tangent to the separation surface is defined.
Measurements were made of the angle between the visible separation boundary and the compression jump developing in the neighborhood of the separation point.
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Abbreviations
- p:
-
pressure
- ρ:
-
density
- t:
-
temperature
- Vt8 :
-
velocity of model
- d:
-
diameter of the model
- M:
-
Mach number
- R:
-
Reynolds number
- γ:
-
coordinate of the point of intersection of the shock-wave continuation and the sphere surface, with the superscript denoting measured values
- γ1 :
-
coordinate of the point of intersection of the continuation of the edge of the separated boundary layer and the sphere surface
- ψ:
-
angle between the shock wave and the tangent to the separation boundary
- ϕ:
-
angle between the tangent to the separation boundary and the direction of flight of the model
- β:
-
angle between the tangent to the surface of the sphere (at its point of intersection with the shock-wave continuation) and the tangent to the separation surface
- L:
-
distance between the point of separation of the boundary layer and the loss-of-stability point of the laminar flow in the wake
- δ:
-
separation of the head shock wave from the sphere
References
G. I. Mishin and N. P. Mende, “Sealed ballistic range,” collection: Aerophysical Investigation of Supersonic Flows [in Russian], Yu. A. Dunaev, ed., Izd-vo Nauka, 1967.
I. V. Basargin, I. M. Dement'ev, and G. I. Mishin, “Range for aerodynamic investigations,” collection: Aerophysical Investigations of Supersonic Flows[in Russian], Yu. A. Dunaev, ed., Izd-vo Nauka, 1967.
M. Ya. Yudelovich, “An approximate method for calculating the pressure aft of spheres” Izv. AN SSSR, Mekhanika, no. 3, 1965.
A. C. Charters and R. N. Thomas, “The aerodynamic performance of small spheres from subsonic to high supersonic velocities,” JAS, vol. 12, no. 4, 1945.
M. P. Syshchikova, M. K. Berezkina, and A. N. Semeuov, “Head shock-wave separation from a sphere in argon and nitrogen,” collection: Aerophysical Investigations of Supersonic Flows [in Russian], Yu. A. Dunaev, ed., Izd-vo Nauka, 1967.
V. G. Maslennikov and A. M. Studenkov, “Position of the head shock wave at Mach numbers closeto unity,” collection; Aerophysical Investigations of Supersonic Flows [in Russian], Yu. A. Dunaev, ed., Izd-vo Nauka, 1967.
S. M. Gilinskii and M. G. Lebedev,” Investigation of low supersonic velocity flows with detached shock waves past plane and axisymmetric bodies,” Izv. AN SSSR, Mekhanika, no. 1, 1965.
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In conclusion, tne authors express their gratitude to A. A. Sokolov and I. I. Skovortsov for their participation in these experiments.
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Bedin, A.P., Dement'ev, I.M. & Mishin, G.I. Investigation of row past a sphere in free flight. J Appl Mech Tech Phys 9, 195–197 (1968). https://doi.org/10.1007/BF00913183
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DOI: https://doi.org/10.1007/BF00913183