Vortex investigation over a rolling delta wing model in transonic flow by stereo PIV measurements

2004 ◽  
Author(s):  
B. Sammler ◽  
A. Schroder ◽  
A. Arnott ◽  
D. Otter ◽  
J. Agocs ◽  
...  
Keyword(s):  
Transonic Flow ◽  
Delta Wing ◽  
Piv Measurements ◽  
Wing Model

On the Effect of the Incident Mach’s Wave on the Pulsation Level in Boundary Layer of the Plane Delta Wing

2014 ◽  
Vol 9 (1) ◽  
pp. 29-38
Author(s):  
Aleksandr Vaganov ◽  
Yuri Yermolaev ◽  
Gleb Kolosov ◽  
Aleksandr Kosinov ◽  
Aleksandra Panina ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Mass Flow ◽  
Delta Wing ◽  
Level Fluctuation ◽  
Flow Pulsation ◽  
Flow Conditions ◽  
Wing Model ◽  
Maximum Value ◽  
Leading Edges ◽  
High Level

The experimental results of high level fluctuation excitation by external Mach’s wave in the boundary layer of delta wing model with blunt leading edges at Mach numbers M = 2, 2.5, 4 are presented. The exitation areas and mass flow pulsation levels in the conditions of subsonic, sonic and supersonic leading edges have been defined. It was found that the maximum value of the pulsations is 12–15 % and varies only slightly from the flow conditions around of the delta wing

scholarly journals Investigation of Shock Motion in Transonic Flow Using an Oscillating, Straked, Delta Wing

AIAA Journal ◽  
2019 ◽  
Vol 57 (10) ◽  
pp. 4406-4415 ◽  
Author(s):  
Dylan N. Hope ◽  
Donald L. Kunz
Keyword(s):  
Transonic Flow ◽  
Delta Wing ◽  
Shock Motion

PIV measurements on a delta wing with periodic blowing and suction

2001 ◽  
Author(s):  
S. Siegel ◽  
Thomas McLaughlin ◽  
Julie Morrow
Keyword(s):  
Delta Wing ◽  
Piv Measurements

Grid Dependency and Aerodynamic Analysis for Transonic Flow of Delta Wing using CFD

2018 ◽  
Vol 46 (6) ◽  
pp. 445-451
Author(s):  
Kiyeon Jeong ◽  
Eunhee Jung ◽  
Dong-Gi Kang ◽  
Daeyeon Lee ◽  
Dukhyun Kim
Keyword(s):  
Transonic Flow ◽  
Delta Wing ◽  
Aerodynamic Analysis

scholarly journals Effects of the Propeller Advance Ratio on Delta Wing UAV Leading Edge Vortex

2019 ◽  
Vol 16 (3) ◽  
pp. 6958-6970 ◽  
Author(s):  
K. A. Kasim ◽  
P. Segard ◽  
S. Mat ◽  
S. Mansor ◽  
M. N. Dahalan ◽  
...  
Keyword(s):  
Swirling Flow ◽  
Delta Wing ◽  
Active Flow Control ◽  
Pressure Coefficient ◽  
Leading Edge ◽  
Adverse Pressure Gradient ◽  
Leading Edge Vortex ◽  
Wing Model ◽  
Edge Vortex ◽  
Advance Ratio

Delta wing is a triangular-shaped platform that can be applied into the unmanned aerial vehicle (UAV) or drone applications. However, the flow above the delta wing is governed by complex leading-edge vortex structures which result in complicated aerodynamics behaviour. At higher angles of attack, the vortex burst can take place when the swirling flow is unable to sustain the adverse pressure gradient. More studies are needed to understand these vortex phenomena. This paper addresses an experimental study of active flow control called propeller on a generic 55° swept angle sharp-edged delta wing model. In this experiment, a propeller was placed at two different locations. The first location was at the apex of the wing while the second position was at the rear of the wing. The experiments were conducted in a 1.5 × 2.0 m2 closed-loop wind tunnel facility at Universiti Teknologi Malaysia. The freestream velocities were set at 20 m/s and 25 m/s. The research consisted of an intensive surface pressure measurement above the wing surface to investigate the effects of rotating propeller towards the leading-edge vortex. The experiments were divided into four configurations. The clean wing configuration was performed without the propeller and followed by pusher-propeller configuration using 10-inch 9-inch propellers. The final configuration was the tractor-propeller with a 10-inch propeller. The results emphasise the influences of the propeller size and its location corresponding to vortex properties above the delta-winged UAV model. The findings had indicated that the vortex peak is increased when the propeller is installed for both pusher and tractor configurations. The results also indicate that the pressure coefficient is increased when the propeller advance ratio increases. 

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