MW energy deposition for aerodynamic application

Yuri F. Kolesnichenko, Vadim G. Brovkin, Olga A. Azarova, Victor G. Grudnitsky, Valery A. Lashkov, Igor Ch Mashek

Результат исследований: Публикации в книгах, отчётах, сборниках, трудах конференцийстатья в сборнике материалов конференциинаучнаярецензирование

10 Цитирования (Scopus)

Выдержка

In previous paper non-stationary streamlining of a blunt body by a supersonic flow with a finite-length thin rarefied channel on its axis was considered. Now analytic and numeric treatment is expanded on the case of infinite discontinuity. Both supersonic and subsonic conditions inside a channel are described in unique approach. The approach is applicable also for the description of a sharpen body - wedge as the simplest representative - interaction with mentioned discontinuity type. The stationary gas dynamic geometry turned out to be independent on the body shape. The shock detachment criterion is formulated - detachment occurs if interaction with discontinuity leads to diminishing of the shock angle, and simultaneously the pressure after the shock. Foundation for such assumption is confirmed by numeric calculations. Reduction of a sharpen body drag at a fixed portion demands deeper rarefaction of gas in a channel than in the case of blunt body. The dependencies of shock detachment velocity on the dimensionless density in the channel for blunt body and wedge are obtained. Comparison with experimental values manifests in favor of highly non-uniform structure of MW plasmoid. The product of three parameters define the ultimate efficiency of interaction - the ratio of cross-sections of body and discontinuity, the square of undisturbed flow Mach number and the body aerodynamic performance. In spite of the last parameter can be small, the first two parameters are large, the fact that gives foundation to assume the method of drag reduction by means of MW energy deposition in supersonic flow as beneficial.

Язык оригиналаанглийский
Название основной публикации41st Aerospace Sciences Meeting and Exhibit
СостояниеОпубликовано - 1 дек 2003
Событие41st Aerospace Sciences Meeting and Exhibit 2003 - Reno, NV, Соединенные Штаты Америки
Продолжительность: 6 янв 20039 янв 2003

Серия публикаций

Название41st Aerospace Sciences Meeting and Exhibit

Конференция

Конференция41st Aerospace Sciences Meeting and Exhibit 2003
СтранаСоединенные Штаты Америки
ГородReno, NV
Период6/01/039/01/03

Отпечаток

Supersonic flow
aerodynamics
Aerodynamics
discontinuity
blunt bodies
shock
Drag reduction
detachment
Gas dynamics
supersonic flow
Mach number
drag
Drag
energy
wedges
streamlining
body shape
Geometry
rarefaction
Gases

Предметные области Scopus

  • Космические науки и планетоведение
  • Авиакосмическая техника

Цитировать

Kolesnichenko, Y. F., Brovkin, V. G., Azarova, O. A., Grudnitsky, V. G., Lashkov, V. A., & Mashek, I. C. (2003). MW energy deposition for aerodynamic application. В 41st Aerospace Sciences Meeting and Exhibit (41st Aerospace Sciences Meeting and Exhibit).
Kolesnichenko, Yuri F. ; Brovkin, Vadim G. ; Azarova, Olga A. ; Grudnitsky, Victor G. ; Lashkov, Valery A. ; Mashek, Igor Ch. / MW energy deposition for aerodynamic application. 41st Aerospace Sciences Meeting and Exhibit. 2003. (41st Aerospace Sciences Meeting and Exhibit).
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title = "MW energy deposition for aerodynamic application",
abstract = "In previous paper non-stationary streamlining of a blunt body by a supersonic flow with a finite-length thin rarefied channel on its axis was considered. Now analytic and numeric treatment is expanded on the case of infinite discontinuity. Both supersonic and subsonic conditions inside a channel are described in unique approach. The approach is applicable also for the description of a sharpen body - wedge as the simplest representative - interaction with mentioned discontinuity type. The stationary gas dynamic geometry turned out to be independent on the body shape. The shock detachment criterion is formulated - detachment occurs if interaction with discontinuity leads to diminishing of the shock angle, and simultaneously the pressure after the shock. Foundation for such assumption is confirmed by numeric calculations. Reduction of a sharpen body drag at a fixed portion demands deeper rarefaction of gas in a channel than in the case of blunt body. The dependencies of shock detachment velocity on the dimensionless density in the channel for blunt body and wedge are obtained. Comparison with experimental values manifests in favor of highly non-uniform structure of MW plasmoid. The product of three parameters define the ultimate efficiency of interaction - the ratio of cross-sections of body and discontinuity, the square of undisturbed flow Mach number and the body aerodynamic performance. In spite of the last parameter can be small, the first two parameters are large, the fact that gives foundation to assume the method of drag reduction by means of MW energy deposition in supersonic flow as beneficial.",
author = "Kolesnichenko, {Yuri F.} and Brovkin, {Vadim G.} and Azarova, {Olga A.} and Grudnitsky, {Victor G.} and Lashkov, {Valery A.} and Mashek, {Igor Ch}",
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Kolesnichenko, YF, Brovkin, VG, Azarova, OA, Grudnitsky, VG, Lashkov, VA & Mashek, IC 2003, MW energy deposition for aerodynamic application. в 41st Aerospace Sciences Meeting and Exhibit. 41st Aerospace Sciences Meeting and Exhibit, Reno, NV, Соединенные Штаты Америки, 6/01/03.

MW energy deposition for aerodynamic application. / Kolesnichenko, Yuri F.; Brovkin, Vadim G.; Azarova, Olga A.; Grudnitsky, Victor G.; Lashkov, Valery A.; Mashek, Igor Ch.

41st Aerospace Sciences Meeting and Exhibit. 2003. (41st Aerospace Sciences Meeting and Exhibit).

Результат исследований: Публикации в книгах, отчётах, сборниках, трудах конференцийстатья в сборнике материалов конференциинаучнаярецензирование

TY - GEN

T1 - MW energy deposition for aerodynamic application

AU - Kolesnichenko, Yuri F.

AU - Brovkin, Vadim G.

AU - Azarova, Olga A.

AU - Grudnitsky, Victor G.

AU - Lashkov, Valery A.

AU - Mashek, Igor Ch

PY - 2003/12/1

Y1 - 2003/12/1

N2 - In previous paper non-stationary streamlining of a blunt body by a supersonic flow with a finite-length thin rarefied channel on its axis was considered. Now analytic and numeric treatment is expanded on the case of infinite discontinuity. Both supersonic and subsonic conditions inside a channel are described in unique approach. The approach is applicable also for the description of a sharpen body - wedge as the simplest representative - interaction with mentioned discontinuity type. The stationary gas dynamic geometry turned out to be independent on the body shape. The shock detachment criterion is formulated - detachment occurs if interaction with discontinuity leads to diminishing of the shock angle, and simultaneously the pressure after the shock. Foundation for such assumption is confirmed by numeric calculations. Reduction of a sharpen body drag at a fixed portion demands deeper rarefaction of gas in a channel than in the case of blunt body. The dependencies of shock detachment velocity on the dimensionless density in the channel for blunt body and wedge are obtained. Comparison with experimental values manifests in favor of highly non-uniform structure of MW plasmoid. The product of three parameters define the ultimate efficiency of interaction - the ratio of cross-sections of body and discontinuity, the square of undisturbed flow Mach number and the body aerodynamic performance. In spite of the last parameter can be small, the first two parameters are large, the fact that gives foundation to assume the method of drag reduction by means of MW energy deposition in supersonic flow as beneficial.

AB - In previous paper non-stationary streamlining of a blunt body by a supersonic flow with a finite-length thin rarefied channel on its axis was considered. Now analytic and numeric treatment is expanded on the case of infinite discontinuity. Both supersonic and subsonic conditions inside a channel are described in unique approach. The approach is applicable also for the description of a sharpen body - wedge as the simplest representative - interaction with mentioned discontinuity type. The stationary gas dynamic geometry turned out to be independent on the body shape. The shock detachment criterion is formulated - detachment occurs if interaction with discontinuity leads to diminishing of the shock angle, and simultaneously the pressure after the shock. Foundation for such assumption is confirmed by numeric calculations. Reduction of a sharpen body drag at a fixed portion demands deeper rarefaction of gas in a channel than in the case of blunt body. The dependencies of shock detachment velocity on the dimensionless density in the channel for blunt body and wedge are obtained. Comparison with experimental values manifests in favor of highly non-uniform structure of MW plasmoid. The product of three parameters define the ultimate efficiency of interaction - the ratio of cross-sections of body and discontinuity, the square of undisturbed flow Mach number and the body aerodynamic performance. In spite of the last parameter can be small, the first two parameters are large, the fact that gives foundation to assume the method of drag reduction by means of MW energy deposition in supersonic flow as beneficial.

UR - http://www.scopus.com/inward/record.url?scp=84894806518&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84894806518

SN - 9781624100994

T3 - 41st Aerospace Sciences Meeting and Exhibit

BT - 41st Aerospace Sciences Meeting and Exhibit

ER -

Kolesnichenko YF, Brovkin VG, Azarova OA, Grudnitsky VG, Lashkov VA, Mashek IC. MW energy deposition for aerodynamic application. В 41st Aerospace Sciences Meeting and Exhibit. 2003. (41st Aerospace Sciences Meeting and Exhibit).