Variable Camber Compliant Wing - Wind Tunnel Testing

Marks, Christopher R.; Zientarski, Lauren; Culler, Adam J.; Hagen, Benjamin; Smyers, Brian; Joo, James J.

doi:10.2514/6.2015-1051

Cited by 34 publications

(16 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Superior aerodynamic performance of seamless skin variable camber wing due to morphing leading edge and trailing edge and span wise wing twist has been demonstrated by Joo et al's VCCW concept through wind tunnel testing (seen in Fig. 1(a)) [7,8]. a) b) Fig.…”

mentioning

confidence: 84%

“…In the demonstrative design stated later in this paper, the leading edge morphing is restrained as wind tunnel testing shows that XFOIL is unable to accurately estimate the morphing leading edge part [7]. To achieve a subtler control of both leading edge and trailing edge, Bernstein Polynomial of larger order may be applicable in the design, which will not be discussed in this paper.…”

Section: Fig 5 Comparison Between Original Geometry and Parametric mentioning

confidence: 99%

“…Several morphing concepts, such as Mission Adaptive Wing in 1980s [4], Smart Wing Program in 1990s [5], Mission Adaptive Compliant Wing in 2000s [6] and a very recent Variable Camber Compliant Wing (VCCW) concept by the Air Force Research Laboratory (AFRL) [7,8], have been proposed. Other advantages of morphing wing technologies have also been verified by wind tunnel tests and flight tests in the above programs and other researchers' work.…”

mentioning

confidence: 99%

See 2 more Smart Citations

Preliminary airfoil design of an innovative adaptive variable camber compliant wing

Li¹,

Ang²

2016

J. vibroeng.

View full text Add to dashboard Cite

In this study, an innovative adaptive variable camber compliant wing, with skin that can change thickness and tailing edge morphing mechanism that is designed based on a new kind of artificial muscles, is designed. Consisted of a compliant base plate and seamless and continuous compliant skin with the artificial muscles embedded in, this trailing edge morphing mechanism is extremely light in weight and efficient in reconfiguration of the wing sectional profile. To demonstrate the feasibility of this design, a simulative experiment of this kind of artificial muscles was designed and carried out. A demonstrative wing section with simulative driving skin mechanism and the compliant skin was manufactured. The demonstration wing section shows that the trailing edge morphing mechanism designed and simulative driving skin work good, with a -30°/+30° trailing edge morphing achieved. Targeting this innovative design, an airfoil design approach, employing CST parametric methodology, XFOIL and Multi-Objective Particle Swarm (MOPS) optimizer, is developed for the preliminary design of this innovative wing. A new selector is introduced to facilitate the searching process and improve the robustness of this method. The results show that this method is capable of designing airfoils for this special wing in a quick and effective way.

show abstract

mentioning

confidence: 84%

Section: Fig 5 Comparison Between Original Geometry and Parametric mentioning

confidence: 99%

mentioning

confidence: 99%

See 1 more Smart Citation

Preliminary airfoil design of an innovative adaptive variable camber compliant wing

Li¹,

Ang²

2016

J. vibroeng.

View full text Add to dashboard Cite

show abstract

“…Since the wing was smaller than the test section, a custom fixture had to be designed to support the model as well as measure forces and moments. An in-depth discussion of the wind tunnel and the testing procedures is detailed in the paper by Marks et al 11 Force and moment data, and the resulting lift and drag acquired by the force couples embedded in the support structure, is not included in the analysis presented here. Fixture alignment issues and other unknowns will require further analysis to be fully understood.…”

Section: A Experimental Testingmentioning

confidence: 98%

“…The specific design of the model is covered more in two companion papers. 1,11 The flexible composite material, used to allow the high range of motion during camber changes, proved to be difficult to model within FEA and was the limiting factor in this analysis. A 1 ft version FEA model was built to verify the desired shapes, and while this particular FEA model did not include all of the skin material, it was still able to match the desired camber shapes.…”

Section: B Finite Element Analysismentioning

confidence: 99%

Fluid-Structure Interaction of a Variable Camber Compliant Wing

Miller

2015

53rd AIAA Aerospace Sciences Meeting

Self Cite

View full text Add to dashboard Cite

This paper presents results for a loosely-coupled fluid-structure interaction (FSI) of a flexible wing using FUN3D to compute the aerodynamic flow-field and Abaqus to calculate the structural deformation. NASA Langley also provides a general 3D algorithm to interpolate between dissimilar meshes which is used here to map pressures and displacements between the aerodynamic and structural codes. This method is applied to the AFRLdeveloped "Variable Camber Compliant Wing" (VCCW), which is an adaptable wing designed target airfoil shapes between a NACA 2410 and 8410. Results will be compared to experiments conducted in the AFRL Vertical Wind Tunnel.

show abstract

Minimum‐series twist distributions for yawing‐moment control during pure roll*

2021

Self Cite

View full text Add to dashboard Cite

The main wings of most aircraft produce adverse yaw during roll. In order to control the lateral direction of the aircraft during the roll, the rudder is often mixed with the aileron. Lifting-line theory is used here to develop spanwise lift distributions that require the minimum number of terms in the Fourier-series solution for controlling the yawing moment during pure rolling motion using only the main wing. It is shown that the yawing moment can be controlled for arbitrary rolling moments and/or rolling rates by adding symmetric twist in the main wing. The induced-drag penalty for using this method to control the yawing moment is significant and discussed in detail. For example, it is shown that if zero yawing moment is prescribed, the induced drag can increase by 108% for a prescribed rolling moment or by 300% during a steady rolling rate relative to the induced drag in steady level flight. Because this is the minimum-series solution, it does not represent the solution for yaw control with minimum induced drag, since more terms could be used in the Fourier series describing the lift distribution to control yaw with less induced drag. However, the solutions presented here can be useful for aircraft with continuous trailing-edge technologies that are Nomenclature:, Fourier coefficients in the lifting-line solution for the section-lift distribution, Eq. (1); , coefficients in the decomposed Fourier-series solution to the lifting-line equation related to planform, Eqs. (8) and ( 9); b, wingspan; , coefficients in the decomposed Fourier-series solution to the lifting-line equation related to symmetric baseline twist, Eqs. ( 8) and (10);, induced-drag coefficient; , induced-drag coefficient produced by the elliptic lift distribution for a given aspect ratio and lift coefficient, Eq. (21); , total lift coefficient;̃, section-lift coefficient;̃, , section-lift slope; , rolling-moment coefficient; , yawing-moment coefficient; , , change in yawing moment with rolling moment; ,̄, change in yawing moment with rolling rate; c, section chord length;̄, wing mean chord length; , coefficients in the decomposed Fourier-series solution to the lifting-line equation due to antisymmetric twist related to roll control, Eqs. ( 8) and (11); c root , chord length at wing root; , coefficients in the decomposed Fourier-series solution to the lifting-line equation related to rolling rate, Eqs. (8) and ( 12); , coefficients in the decomposed Fourier-series solution to the lifting-line equation due to symmetric twist related to yaw control, Eqs. (8) and (13); j, term in the infinite series;̃, section lift; N, number of terms retained when truncating the infinite Fourier series; , angular rigid-body rolling rate;̄, dimensionless angular rigid-body rolling rate [pb/(2V ∞ )]; , wing aspect ratio ( 2 ∕ ); , wing taper ratio; , wing planform area; ∞ , freestream airspeed; z, spanwise coordinate relative to the midspan, positive out left wing; , spanwise variation in local geometric angle of attack relative to the freestream; 0 , spanwise varia...

show abstract

Variable Camber Compliant Wing - Wind Tunnel Testing

Cited by 34 publications

References 10 publications

Preliminary airfoil design of an innovative adaptive variable camber compliant wing

Preliminary airfoil design of an innovative adaptive variable camber compliant wing

Fluid-Structure Interaction of a Variable Camber Compliant Wing

Minimum‐series twist distributions for yawing‐moment control during pure roll*

Contact Info

Product

Resources

About