Navier-Stokes Simulations for Transport Aircraft Wing/Body High-Lift Configurations

2003 ◽  
Vol 40 (5) ◽  
Author(s):  
HaiXin Chen ◽  
Song Fu ◽  
FengWei Li
Keyword(s):  
Navier Stokes ◽  
Aircraft Wing ◽  
High Lift ◽  
Transport Aircraft

Navier-Stokes Simulations for Transport Aircraft Wing/Body High-Lift Configurations

2003 ◽  
Vol 40 (5) ◽  
pp. 883-890 ◽  
Author(s):  
HaiXin Chen ◽  
Song Fu ◽  
Feng Wei Li
Keyword(s):  
Navier Stokes ◽  
Aircraft Wing ◽  
High Lift ◽  
Transport Aircraft

Three-Dimensional Navier-Stokes Simulations for Transport Aircraft High-Lift Configurations

2001 ◽  
Vol 38 (5) ◽  
pp. 895-903 ◽  
Author(s):  
R. Rudnik ◽  
S. Melber ◽  
A. Ronzheimer ◽  
O. Brodersen
Keyword(s):  
Three Dimensional ◽  
Navier Stokes ◽  
High Lift ◽  
Transport Aircraft

scholarly journals Numerical analysis of high-lift configurations with oscillating flaps

2021 ◽  
Author(s):  
Johannes Ruhland ◽  
Christian Breitsamter
Keyword(s):  
Reynolds Number ◽  
Flow Separation ◽  
Separated Flow ◽  
Navier Stokes ◽  
Rotational Axis ◽  
High Lift ◽  
Hinge Point ◽  
Reduced Frequency ◽  
Flap Deflection ◽  
The Impact

AbstractThis study presents two-dimensional aerodynamic investigations of various high-lift configuration settings concerning the deflection angles of droop nose, spoiler and flap in the context of enhancing the high-lift performance by dynamic flap movement. The investigations highlight the impact of a periodically oscillating trailing edge flap on lift, drag and flow separation of the high-lift configuration by numerical simulations. The computations are conducted with regard to the variation of the parameters reduced frequency and the position of the rotational axis. The numerical flow simulations are conducted on a block-structured grid using Reynolds Averaged Navier Stokes simulations employing the shear stress transport $$k-\omega $$ k - ω turbulence model. The feature Dynamic Mesh Motion implements the motion of the oscillating flap. Regarding low-speed wind tunnel testing for a Reynolds number of $$0.5 \times 10^{6}$$ 0.5 × 10 6 the flap movement around a dropped hinge point, which is located outside the flap, offers benefits with regard to additional lift and delayed flow separation at the flap compared to a flap movement around a hinge point, which is located at 15 % of the flap chord length. Flow separation can be suppressed beyond the maximum static flap deflection angle. By means of an oscillating flap around the dropped hinge point, it is possible to reattach a separated flow at the flap and to keep it attached further on. For a Reynolds number of $$20 \times 10^6$$ 20 × 10 6 , reflecting full scale flight conditions, additional lift is generated for both rotational axis positions.

Design-Oriented High-Lift Methodology for General Aviation and Civil Transport Aircraft

2001 ◽  
Vol 38 (6) ◽  
pp. 1076-1084 ◽  
Author(s):  
C. P. van Dam ◽  
J. C. Vander Kam ◽  
J. K. Paris
Keyword(s):  
General Aviation ◽  
High Lift ◽  
Transport Aircraft

High-lift design optimization using Navier-Stokes equations

1996 ◽  
Vol 33 (3) ◽  
pp. 499-504 ◽  
Author(s):  
S. Eyi ◽  
K. D. Lee ◽  
S. E. Rogers ◽  
D. Kwak
Keyword(s):  
Design Optimization ◽  
Stokes Equations ◽  
Navier Stokes ◽  
High Lift ◽  
Navier Stokes Equations
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