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Scientific Visualization
| Issue Year: | 2014 |
| Quarter: | 3 |
| Volume: | 6 |
| Number: | 3 |
| Pages: | 55 - 67 |
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| Article Name: |
NUMERICAL AND EXPERIMENTAL PATTERNS OF SUPERSONIC FLOW AROUND CONTROL SHIELDS ON SEGMENTCONICAL BODIES OF REVOLUTION |
| Authors: |
S.I.Gerasimov (Russian Federation), I.I. Kanygin (Russian Federation), V.A.Kikeev (Russian Federation), R.V.Gerasimova (Russian Federation), K.V. Totyshev (Russian Federation), V.K. Golubev (Russian Federation) |
| Address: |
S.I.Gerasimov
s.i.gerasimov@mail.ru
Sarov Physics and Technical Institute of National Research Nuclear University «MEPHI», Nizhny Novgorod region, 607186 Russian Federation
Russian Federal Nuclear Center – All-Russia Research Institute of Experimental Physics, Sarov, Nizhny Novgorod region, 607188 Russian Federation
Nizhny Novgorod State Technical University n.a. R.E. Alekseev, 603950 Russia
I.I. Kanygin
John013@yandex.ru
Sarov Physics and Technical Institute of National Research Nuclear University «MEPHI», Nizhny Novgorod region, 607186 Russian Federation
Russian Federal Nuclear Center – All-Russia Research Institute of Experimental Physics, Sarov, Nizhny Novgorod region, 607188 Russian Federation
V.A.Kikeev
vkikeev@mail.ru
Nizhny Novgorod State Technical University n.a. R.E. Alekseev, 603950 Russian Federation
R.V.Gerasimova
r.v.gerasimova@mail.ru
Russian Federal Nuclear Center – All-Russia Research Institute of Experimental Physics, Sarov, Nizhny Novgorod region, 607188 Russian Federation
K.V. Totyshev
Sarov Physics and Technical Institute of National Research Nuclear University «MEPHI», Nizhny Novgorod region, 607186 Russian Federation
V.K. Golubev
Russian Federal Nuclear Center – All-Russia Research Institute of Experimental Physics, Sarov, Nizhny Novgorod region, 607188 Russian Federation |
| Abstract: |
For control, braking and stabilization of supersonic and hypersonic aircraft with more and more applications are used shield controls. The use of such controls, allow for a fairly wide range to change the aerodynamic coefficients of the aircraft. At supersonic flight velocities there is a complex pattern of the flow around aircraft, especially in the areas of location of the shields, where separated flow occurs. Obtaining realistic data for separated flows in various conditions, especially at high angles of attack is possible now only with the use of experimental methods. At the same time, existing numerical methods enable one to correctly analyze the pattern about the aircraft as a whole and be able to get acceptable results on determination of aerodynamic coefficients in a wide range of flow conditions. Good agreement of these results with experimental data of a single measurement allows the prediction to determine the values of these coefficients at any arbitrary conditions of flow. Below are the results of the study of supersonic flow past the series models of hypersonic aircraft. The tested models were of different shape and size of control shields. |
| Language: |
Russian |
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