Validation of Computed High-Lift Flows with Significant Wind-Tunnel Effects

AIAA Journal ◽  
2001 ◽  
Vol 39 (10) ◽  
pp. 1884-1892 ◽  
Author(s):  
Stuart E. Rogers ◽  
Karlin Roth ◽  
Steven M. Nash
Keyword(s):  
Wind Tunnel ◽  
High Lift ◽  
Tunnel Effects

Validation of computed high-lift flows with significant wind-tunnel effects

AIAA Journal ◽  
2001 ◽  
Vol 39 ◽  
pp. 1884-1892
Author(s):  
Stuart E. Rogers ◽  
Karlin Roth ◽  
Steven M. Nash
Keyword(s):  
Wind Tunnel ◽  
High Lift ◽  
Tunnel Effects

Wind Tunnel Experiment of Microjet-based Flow Control on a Multi-Element High-Lift Airfoil

2022 ◽  
Author(s):  
Case P. Van Dam ◽  
Sai B. Mothukuri ◽  
Seyedeh Sheida Hosseini ◽  
Edward White ◽  
Lisa Brown ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Flow Control ◽  
Wind Tunnel Experiment ◽  
High Lift

Characterisation of a highly staggered spanwise cambered biplane

2015 ◽  
Vol 119 (1212) ◽  
pp. 203-228
Author(s):  
L.W. Traub ◽  
R. Waghela ◽  
K.A. Bordignon
Keyword(s):  
Numerical Simulation ◽  
Wind Tunnel ◽  
Dihedral Angles ◽  
Wind Tunnel Testing ◽  
High Lift ◽  
Front Wing ◽  
Geometric Variation ◽  
Tunnel Testing

AbstractAn investigation is presented to elucidate the performance of a staggered, spanwise cambered biplane. The spanwise camber yielded wings forming a ‘∧’ or ‘∨’ when viewed streamwise. The configuration is examined in terms of its aerodynamic and stability characteristics. The feasibility of negating the requirement for a conventional empennage is explored. Geometric variation encompassed front and back wing anhedral/dihedral angles yielding 49 combinations. Evaluation of the geometry was accomplished using both wind tunnel testing and numerical simulation. The results indicated that front wing dihedral in conjunction with aft wing anhedral was most beneficial, such that the benefit of wake spacing was maximised. Aerodynamic benefit was indicated compared to a conventional empennage geometry. The greatest disparity in behaviour of the fore and aft wing anhedral/dihedral distribution was in the high lift regime, where the nature of the stall varied. Simulations to establish the viability of the geometry in terms of controllability were also conducted and indicated that the configuration is viable.

Wind-Tunnel Tests of a High Lift Generation and Stall/Spin Recovery System

2000 ◽  
Vol 37 (3) ◽  
pp. 383-389 ◽  
Author(s):  
D. K. Nowak ◽  
U. P. Solies
Keyword(s):  
Wind Tunnel ◽  
High Lift ◽  
Wind Tunnel Tests ◽  
Recovery System

High-Lift Airfoil Interacting with a Vortical Disturbance: Wind-Tunnel Measurements

AIAA Journal ◽  
2015 ◽  
Vol 53 (6) ◽  
pp. 1681-1692 ◽  
Author(s):  
S. Klein ◽  
D. Hoppmann ◽  
P. Scholz ◽  
R. Radespiel
Keyword(s):  
Wind Tunnel ◽  
High Lift ◽  
Wind Tunnel Measurements ◽  
Vortical Disturbance

Wind Tunnel Experimental Study of Wind Turbine Airfoil Aerodynamic Characteristics

2012 ◽  
Vol 260-261 ◽  
pp. 125-129
Author(s):  
Xin Zi Tang ◽  
Xu Zhang ◽  
Rui Tao Peng ◽  
Xiong Wei Liu
Keyword(s):  
Wind Tunnel ◽  
Wind Turbine ◽  
Lift Coefficient ◽  
Turbine Blades ◽  
Aerodynamic Characteristics ◽  
Wind Turbine Blades ◽  
High Lift ◽  
Minimum Drag ◽  
Stall Angle ◽  
High Reynolds

High lift and low drag are desirable for wind turbine blade airfoils. The performance of a high lift airfoil at high Reynolds number (Re) for large wind turbine blades is different from that at low Re number for small wind turbine blades. This paper investigates the performance of a high lift airfoil DU93-W-210 at high Re number in low Re number flows through wind tunnel testing. A series of low speed wind tunnel tests were conducted in a subsonic low turbulence closed return wind tunnel at the Re number from 2×105to 5×105. The results show that the maximum lift, minimum drag and stall angle differ at different Re numbers. Prior to the onset of stall, the lift coefficient increases linearly and the slope of the lift coefficient curve is larger at a higher Re number, the drag coefficient goes up gradually as angle of attack increases for these low Re numbers, meanwhile the stall angle moves from 14° to 12° while the Re number changes from 2×105to 5×105.

High-Lift Device Testing in JAXA 6.5M X 5.5M Low-Speed Wind Tunnel

2006 ◽  
Author(s):  
Takeshi Ito ◽  
Yuzuru Yokokawa ◽  
Hiroki Ura ◽  
Hiroyuki Kato ◽  
Kazunori Mitsuo ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
High Lift ◽  
Low Speed ◽  
Low Speed Wind Tunnel

Wind tunnel investigation of a high lift system with pneumatic flow control

2016 ◽  
Author(s):  
Pricop Mihai Victor ◽  
Boscoianu Mircea ◽  
Crunteanu Daniel-Eugeniu
Keyword(s):  
Wind Tunnel ◽  
Flow Control ◽  
High Lift
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