scholarly journals Experimental study of flow field distribution over a generic cranked double delta wing

2016 ◽  
Vol 29 (5) ◽  
pp. 1196-1204 ◽  
Author(s):  
Mojtaba Dehghan Manshadi ◽  
Mehdi Eilbeigi ◽  
Mohammad Kazem Sobhani ◽  
Mehrdad Bazaz Zadeh ◽  
Mohammad Ali Vaziry
Keyword(s):  
Experimental Study ◽  
Flow Field ◽  
Field Distribution ◽  
Delta Wing ◽  
Double Delta Wing

scholarly journals Theoretical and Experimental of Evaluation of Flow Field Over a Double Delta Wing at Supersonic Speeds

2019 ◽  
Vol 8 (2S11) ◽  
pp. 2939-2943
Keyword(s):  
Stainless Steel ◽  
Flow Field ◽  
Numerical Simulations ◽  
Delta Wing ◽  
Angle Of Attack ◽  
Experimental Studies ◽  
The Body ◽  
Experimental Investigations ◽  
Supersonic Speed ◽  
Double Delta Wing

Numerical and experimental investigations of flay over double delta wing at supersonic speed are investigated . For numerical simulations , the body geometry is generated using SolidWorks software , mesh is created using Gambit and solution is obtained using Fluent sofivvare . For the experimental studies , stainless steel model is fabricated and tested in the supersonic Mind tunnel at Mach 2.5 at 0 and 5 angle of attack . The results are presented in the present paper

scholarly journals Numerical investigations of vortex formation on a generic multiple-swept-wing configuration

2021 ◽  
Author(s):  
D. Sedlacek ◽  
S. Biechele ◽  
C. Breitsamter
Keyword(s):  
Flow Field ◽  
Delta Wing ◽  
Vortex Formation ◽  
Navier Stokes ◽  
Swept Wing ◽  
Field Development ◽  
Numerical Investigations ◽  
Moment Coefficient ◽  
Wind Tunnel Data ◽  
Double Delta Wing

AbstractFor an improvement of the flight stability characteristics of high-agility aircraft, the comprehension of the vortex development, behavior and break down is important. Therefore, numerical investigations on low aspect ratio, multiple-swept-wing configurations are performed in this study to analyze the influence of the numerical method on the vortex formation. The discussed configurations are based on a triple- and double-delta wing planform. Unsteady Reynolds-averaged Navier–Stokes (URANS) simulations and delayed detached eddy simulations (DDES) are performed for both configurations. The simulations are executed at Re $$= 3.0\times 10^6$$ = 3.0 × 10 6 , symmetric freestream conditions, and an angle of attack of $$\alpha = 16^\circ$$ α = 16 ∘ , for consistency with reference wind tunnel data. For the triple-delta-wing configuration, the results of the DDES show a satisfying accordance to the experiments compared to URANS, especially for the flow field and the pitching moment coefficient. For the double-delta-wing configuration, the URANS simulation provides reliable results with low deviation of the aerodynamic coefficients and high precision for the flow field development with respect to the experimental data.

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 Various Shape Fillets on a 76/40 Double Delta Wing from Mach 0.18 to 0.7

1994 ◽  
Author(s):  
Hugo Gonzalez ◽  
Gary Erickson ◽  
Blair McLachlan ◽  
James Bell
Keyword(s):  
Delta Wing ◽  
Double Delta Wing
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