Approach to Induced Drag Reduction with Experimental Evaluation

Eller, David; Heinze, Sebastian

doi:10.2514/1.11713

Cited by 16 publications

(7 citation statements)

References 10 publications

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“…The benefit will be obtained if the proper control strategy is employed. The benefit includes: (7) The roll trim can be achieved by using multiple control surfaces with smaller deflection than with single aileron. And further deflection saving in most dynamic pressure range can be achieved if the conformal control surface employed.…”

Section: Discussionmentioning

confidence: 99%

“…If the minimal induced drag obtained by elliptical lift distribution with minimal angle of attack and control surface deflections, the total drag could achieve a minimum. D.Eller et al [7] posted a trim optimization on a uniform wing with 10 pairs of leading and trailing edge control surfaces. In the study, the multiple control surfaces were employed to minimize the induced drag subject to a given lift coefficient.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Aerodynamic and Aeroelastic Characteristics of Conformal Control Surfaces and Application in Active Aeroelastic Wing Technology

Xie¹,

Yang²,

Guo³

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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This paper presents an investigation into characteristics and applications of conformal control surfaces. The attention was at first paid to the study of the aerodynamic and aeroelastic characteristics of a wing with deflected leading and trailing edges. By using thin airfoil theory and polynomial function for the camber modeling, the camber effects and aerodynamic forces derivatives was evaluated and compared. Based on the 2D wing study, the control effectiveness of 3D wing considering aeroelastic effect is evaluated. The results show that the trailing edge conformal control surfaces produce a greater roll rate but cause control reversal at a lower dynamic pressure, whereas leading edge control surfaces can provide control power at a wider dynamic pressure range. By taking these advantages, it is possible to improve roll control by incorporating the leading control surfaces. Attention is also paid to exploring the control strategies to schedule the leading and trailing edge control surfaces efficiently. The results shows that active aeroelastic wing technology enables the roll control free from the limitation of structure flexibility and hence the potential of weight saving. Moreover, conformal control surfaces could maintain the control authority in the most speed range with less deflection demands suggesting the drag reduction and energy saving. This investigation provides an insight into the active aeroelastic wing integrated with conformal leading and trailing edge control surfaces.

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Section: Discussionmentioning
confidence: 99%

Section: Introductionmentioning
confidence: 99%

Aerodynamic and Aeroelastic Characteristics of Conformal Control Surfaces and Application in Active Aeroelastic Wing Technology
Xie¹,
Yang²,
Guo³
2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
1
0
0
0
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“…The wind tunnel model was developed at the Department for previous studies, e.g. [2,4]. The model is mounted on a fairly stiff wind tunnel sting as shown in Fig.…”

Section: Methodsmentioning
confidence: 99%

Real time drag minimization using redundant control surfaces
Jacobsen
¹

2006
Aerospace Science and Technology
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“…6, the large AR Goland wing and a low AR fighter wing were made adaptive by incorporating a large number of trailing edge flaps into them À20 per half wing to be precise. 11,12 An inverse optimization approach was used to enforce an elliptic lift distribution and indirectly achieve significant reductions in induced drag.…”

Section: Introductionmentioning
confidence: 99%

Aerostructural performance improvement in an unmanned long endurance aircraft using adaptive wing concept
Sampath
¹
,
Padmanabhan
²
,
Kattimani
³

2023
Proceedings of the Institution of Mechanical Engineers, Part G:
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This paper presents an analytical research study to improve the aerostructural performance of an unmanned medium altitude long endurance aircraft using the adaptive wing concept. Aerodynamic drag and wing root loads are minimized by optimal scheduling of multiple trailing edge flaps located on the wing. A trim optimization process is developed specifically for this purpose. The aeroelastic model is based on finite element formulation for the structure and doublet lattice method for the aerodynamics. A nonlinear numerical lifting line method is used, in combination with airfoil wind tunnel data, to estimate the induced and total drags. Results are presented for the current aircraft configuration and a more flexible proposed configuration, thereby providing an uncommon perspective on the effect of flexibility on the adaptive wing. For example, the benefits of optimal flap deployment turn out to be greater for the flexible aircraft than for the rigid one. It is hoped that this work and its insights will also aid the multidisciplinary design optimization of future aircraft.

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Approach to Induced Drag Reduction with Experimental Evaluation

Cited by 16 publications

References 10 publications

Aerodynamic and Aeroelastic Characteristics of Conformal Control Surfaces and Application in Active Aeroelastic Wing Technology

Aerodynamic and Aeroelastic Characteristics of Conformal Control Surfaces and Application in Active Aeroelastic Wing Technology

Real time drag minimization using redundant control surfaces

Aerostructural performance improvement in an unmanned long endurance aircraft using adaptive wing concept

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