Mach Number Effects on Vortex Breakdown in Subsonic Flow over a Delta Wing

2011 ◽  
Author(s):  
Hiroaki Fukumoto ◽  
Yoshihiro Ishikawa ◽  
Taku Nonomura ◽  
Kozo Fujii
Keyword(s):  
Mach Number ◽  
Subsonic Flow ◽  
Vortex Breakdown ◽  
Delta Wing

Diamond, cropped, delta, and double-delta wing vortex breakdown during dynamic pitching

AIAA Journal ◽  
1997 ◽  
Vol 35 ◽  
pp. 567-569
Author(s):  
Roy Y. Myose ◽  
Boon-Kiat Lee ◽  
Shigeo Hayashibara ◽  
L. S. Miller
Keyword(s):  
Vortex Breakdown ◽  
Delta Wing ◽  
Double Delta Wing

Effects of a vectored trailing edge jet on delta wing vortex breakdown

2003 ◽  
Vol 34 (5) ◽  
pp. 651-654 ◽  
Author(s):  
J. J. Wang ◽  
Q. S. Li ◽  
J. Y. Liu
Keyword(s):  
Vortex Breakdown ◽  
Delta Wing ◽  
Trailing Edge

scholarly journals Numerical investigation of unsteady vortex breakdown past 80°/65° double-delta wing

2014 ◽  
Vol 27 (3) ◽  
pp. 521-530 ◽  
Author(s):  
Jian Liu ◽  
Haisheng Sun ◽  
Zhitao Liu ◽  
Zhixiang Xiao
Keyword(s):  
Numerical Investigation ◽  
Vortex Breakdown ◽  
Delta Wing ◽  
Double Delta Wing

An investigation into the use of GAMA water tunnel for visualization of vortex breakdown on the delta wing

2018 ◽  
Author(s):  
Setyawan Bekti Wibowo ◽  
Sutrisno ◽  
Tri Agung Rohmat ◽  
Zainuri Anwar ◽  
Firdaus R. Syadi ◽  
...  
Keyword(s):  
Vortex Breakdown ◽  
Delta Wing ◽  
Water Tunnel

Delta wing in a subsonic flow

1994 ◽  
Vol 29 (2) ◽  
pp. 282-284
Author(s):  
S. K. Betyaev ◽  
O. P. Brysov
Keyword(s):  
Subsonic Flow ◽  
Delta Wing

On Transition From Supersonic to Subsonic Flow at Low Reynolds Numbers in a Tube

1969 ◽  
Vol 36 (2) ◽  
pp. 146-150 ◽  
Author(s):  
R. Y. Chen ◽  
J. C. Williams
Keyword(s):  
Mach Number ◽  
Static Pressure ◽  
Subsonic Flow ◽  
Supersonic Nozzle ◽  
Reynolds Numbers ◽  
Impact Pressure ◽  
Low Reynolds Numbers ◽  
Pressure Distributions ◽  
Low Reynolds ◽  
The Impact

A supersonic low-density gas stream produced in a supersonic nozzle was passed through a circular tube in which the transition from supersonic to subsonic flow took place. Static pressure distributions along the tube (and nozzle) and impact pressure distributions across the tube at several stations were measured to determine the nature of this transition. The impact pressure distributions were used, together with the local static pressure, to infer Mach number and velocity profiles in the tube. When the pressure distributions and center-line Mach number distributions are considered together, one obtains a fairly clear picture of the processes involved in the transition from supersonic to subsonic flow at low Reynolds numbers.

scholarly journals Vortex Breakdown on a Delta Wing

1986 ◽  
Vol 29 (9) ◽  
pp. 2773-2773
Author(s):  
F. M. Payne ◽  
R. C. Nelson ◽  
T. T. Ng
Keyword(s):  
Vortex Breakdown ◽  
Delta Wing
Sign in / Sign up

Export Citation Format

Share Document