Induced Drag Reduction of an Airplane Using Local Twist, Panel Method Verification

2012 ◽  
Author(s):  
Pedro Boschetti ◽  
Elsa Cardenas ◽  
Andrea Amerio
Keyword(s):  
Drag Reduction ◽  
Panel Method ◽  
Induced Drag

scholarly journals Fibre-induced drag reduction

2008 ◽  
Vol 602 ◽  
pp. 209-218 ◽  
Author(s):  
J. J. J. GILLISSEN ◽  
B. J. BOERSMA ◽  
P. H. MORTENSEN ◽  
H. I. ANDERSSON
Keyword(s):  
Experimental Data ◽  
Numerical Simulation ◽  
Reynolds Number ◽  
Drag Reduction ◽  
Elastic Layer ◽  
Turbulent Drag Reduction ◽  
Rigid Polymer ◽  
Fibre Concentration ◽  
Induced Drag ◽  
Turbulent Drag

We use direct numerical simulation to study turbulent drag reduction by rigid polymer additives, referred to as fibres. The simulations agree with experimental data from the literature in terms of friction factor dependence on Reynolds number and fibre concentration. An expression for drag reduction is derived by adopting the concept of the elastic layer.

Induced Drag Reduction with the WINGGRID Device

2001 ◽  
pp. 304-311
Author(s):  
Ulrich ◽  
Lucas Roche ◽  
La Roche Consulting
Keyword(s):  
Drag Reduction ◽  
Induced Drag

scholarly journals Variable cant angle winglets for improvement of aircraft flight performance

Meccanica ◽  
2020 ◽  
Vol 55 (10) ◽  
pp. 1917-1947
Author(s):  
J. E. Guerrero ◽  
M. Sanguineti ◽  
K. Wittkowski
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Drag Reduction ◽  
Fuel Efficiency ◽  
Aerodynamic Performance ◽  
Flight Performance ◽  
Sweep Angle ◽  
Aircraft Flight ◽  
Induced Drag ◽  
Aircraft Performance

Abstract Traditional winglets are designed as fixed devices attached at the tips of the wings. The primary purpose of the winglets is to reduce the lift-induced drag, therefore improving aircraft performance and fuel efficiency. However, because winglets are fixed surfaces, they cannot be used to control lift-induced drag reductions or to obtain the largest lift-induced drag reductions at different flight conditions (take-off, climb, cruise, loitering, descent, approach, landing, and so on). In this work, we propose the use of variable cant angle winglets which could potentially allow aircraft to get the best all-around performance (in terms of lift-induced drag reduction), at different flight phases. By using computational fluid dynamics, we study the influence of the winglet cant angle and sweep angle on the performance of a benchmark wing at Mach numbers of 0.3 and 0.8395. The results obtained demonstrate that by adjusting the cant angle, the aerodynamic performance can be improved at different flight conditions.

On the link between experimentally‐measured turbulence quantities and polymer‐induced drag reduction in pipe flows

AIChE Journal ◽  
2019 ◽  
Vol 65 (9) ◽  
Author(s):  
Victor Voulgaropoulos ◽  
Ivan Zadrazil ◽  
Niccolò Le Brun ◽  
Alexander Bismarck ◽  
Christos N. Markides
Keyword(s):  
Drag Reduction ◽  
Pipe Flows ◽  
Induced Drag

A FENE-P k–ε turbulence model for low and intermediate regimes of polymer-induced drag reduction

2011 ◽  
Vol 166 (12-13) ◽  
pp. 639-660 ◽  
Author(s):  
P.R. Resende ◽  
K. Kim ◽  
B.A. Younis ◽  
R. Sureshkumar ◽  
F.T. Pinho
Keyword(s):  
Drag Reduction ◽  
Turbulence Model ◽  
Induced Drag

scholarly journals Variable Cant Angle Winglets for Improvement of Aircraft Flight Performance

2019 ◽  
Author(s):  
Joel Guerrero ◽  
Kevin Wittkowski ◽  
Marco Sanguineti
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Drag Reduction ◽  
Fuel Efficiency ◽  
Aerodynamic Performance ◽  
Flight Performance ◽  
Sweep Angle ◽  
Aircraft Flight ◽  
Induced Drag ◽  
Aircraft Performance

Traditional winglets are designed as fixed devices attached at the tips of the wings. The primary purpose of the winglets is to reduce the lift-induced drag, therefore improving aircraft performance and fuel efficiency. However, because winglets are fixed surfaces, they cannot be used to control lift-induced drag reductions or to obtain the largest lift-induced drag reductions at different flight conditions (take-off, climb, cruise, loitering, descent, approach, landing, and so on). In this work, we propose the use of variable cant angle winglets which could potentially allow aircraft to get the best all-around performance (in terms of lift-induced drag reduction), at different flight phases. By using computational fluid dynamics, we study the influence of the winglet cant angle and sweep angle on the performance of a benchmark wing at Mach numbers of 0.3 and 0.8395. The results obtained demonstrate that by adjusting the cant angle, the aerodynamic performance can be improved at different flight conditions.

scholarly journals CFD Study of the Impact of Variable Cant Angle Winglets on Total Drag Reduction

Aerospace ◽  
2018 ◽  
Vol 5 (4) ◽  
pp. 126 ◽  
Author(s):  
Joel Guerrero ◽  
Marco Sanguineti ◽  
Kevin Wittkowski
Keyword(s):  
Fluid Dynamics ◽  
Drag Reduction ◽  
Fuel Efficiency ◽  
Aerodynamic Performance ◽  
Fuel Saving ◽  
Sweep Angle ◽  
Total Drag ◽  
Induced Drag ◽  
Aircraft Performance ◽  
The Impact

Winglets are commonly used drag-reduction and fuel-saving technologies in today’s aviation. The primary purpose of the winglets is to reduce the lift-induced drag, therefore improving fuel efficiency and aircraft performance. Traditional winglets are designed as fixed devices attached at the tips of the wings. However, because they are fixed surfaces, they give their best lift-induced drag reduction at a single design point. In this work, we propose the use of variable cant angle winglets which could potentially allow aircraft to get the best all-around performance (in terms of lift-induced drag reduction), at different angle-of-attack values. By using computational fluid dynamics, we study the influence of the winglet cant angle and sweep angle in the performance of a benchmark wing at a Mach number of 0.8395. The results obtained demonstrate that by carefully adjusting the cant angle, the aerodynamic performance can be improved at different angles of attack.

Sign in / Sign up

Export Citation Format

Share Document