Experimental Investigation of the Flow over an 80°/45° Rounded Leading Edge Double-delta Wing-body Model

2013 ◽  
Author(s):  
Sampath Bilakanti ◽  
Kurade Bharat ◽  
Ritu Dubey ◽  
Ae Sivaramakrishnan ◽  
V. Ganeshan
Keyword(s):  
Experimental Investigation ◽  
Delta Wing ◽  
Leading Edge ◽  
Body Model ◽  
Double Delta Wing

Alleviation of pitch-up on delta wings using distributed porosity

1999 ◽  
Vol 103 (1025) ◽  
pp. 339-347 ◽  
Author(s):  
L. W. Traub ◽  
B. Moeller ◽  
S. F. Galls
Keyword(s):  
Experimental Investigation ◽  
Flow Field ◽  
Delta Wing ◽  
Leading Edge ◽  
Surface Flow ◽  
Force Balance ◽  
Flow Visualisation ◽  
Surface Porosity ◽  
Delta Wings ◽  
Field Surveys

Abstract An experimental investigation was undertaken to determine the effectiveness of distributed surface porosity for the alleviation of pitch-up on a delta wing. Tests were undertaken using a 65° sweep delta wing with distributed porosity evaluated at various locations on the wing. Force balance, on and off surface flow visualisation and flow field surveys using a multi-hole probe were undertaken. The data shows that distributed porosity applied along the wing leading edge at the apex is effective in eliminating pitch-up whilst incurring a minimal performance cost. Trailing edge porosity generally degraded performance.

Effect of leading edge shapes on 81°/45° double-delta wing at low speeds

2017 ◽  
Vol 232 (16) ◽  
pp. 3100-3107 ◽  
Author(s):  
B Ashwin Kumar ◽  
P Kumar ◽  
S Das ◽  
JK Prasad
Keyword(s):  
Reasonable Agreement ◽  
Strong Influence ◽  
Delta Wing ◽  
Leading Edge ◽  
Aerodynamic Performance ◽  
Surface Flow ◽  
The Body ◽  
Freestream Velocity ◽  
Flow Visualizations ◽  
Double Delta Wing

Investigations were performed on an 81°/45° sweep double-delta wing at a freestream velocity of 20 m/s. Experiments consisted of the measurement of forces, static pressures, and surface flow visualizations. Effect of the leading edge shapes of the double-delta wing was studied. Results indicated a strong influence of the leading edge shape on the aerodynamic performance of the body. The increase in the bluntness of the leading edge augments the suction pressure and delays the vortex lift phenomena at higher angles of attack, which in turn enhances the lift over the wing. A reasonable agreement between the experiments and computations were observed.

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