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Aeroelastic behaviour of a parameterised circulation-controlled wing

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Abstract

The aeroelastic behaviour of the wing of a short take-off and landing aircraft using the Coandă effect depends on its properties and shape. An existing reduced-order model is parameterised for detailed investigations. On the one hand, varying mass due to tank level and varying overall stiffness is implemented in the reduced-order model. The influence of the mass change on the aeroelastic behaviour is reflected in the stability maps. On the other hand, two-dimensional steady and unsteady aerodynamics of different nose shapes are investigated with detailed computational fluid simulations and included in the reduced-order model. The dependence on the profile shape and the frequency is described. Their influence on the aeroelastic behaviour is reflected by the stability maps as well.

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Abbreviations

\(A_{\text {ref}}\) :

Reference wing area

\(c_{\text {L}}\) :

Lift coefficient

\(c_{\text {M}}\) :

Pitching moment coefficient

\(c_{\text {p}}\) :

Pressure coefficient

\(c_\mu\) :

Momentum coefficient of the circulation control

f :

Frequency

g :

Net weight

h :

Heave displacement

l :

Chord length

m :

Mass

\(\dot{m}_{\text {jet}}\) :

Mass flow in the Coandă slot

q :

Generalised coordinate

\(q_\infty\) :

Dynamic pressure

\(v_\infty\) :

Approach velocity

\(v_{\text {jet}}\) :

Jet velocity in the Coandă slot

\(\alpha\) :

(Effective) angle of attack

\(\gamma _i\) :

i-th participation factor

\(\delta _{\text {fl}}\) :

Flap deflection

\(\eta\) :

Dimensionless chord

\(\eta _{\text {k}}\) :

Parameterised stiffness

\(\eta _{\text {m}}\) :

Parameterised tank level

\(\omega\) :

Natural frequency

\(\omega _i\) :

i-th natural frequency

\(\mathbf {A_0}\) :

Aerodynamic stiffness matrix

\(\mathbf {A_1}\) :

Aerodynamic damping matrix

\(\mathbf {K}\) :

Stiffness matrix

\(\mathbf {L}\) :

Aerodynamic load vector

\(\mathbf {M}\) :

Mass matrix

\(\mathbf {X}\) :

Modal matrix

\(\mathbf {q}\) :

Vector of generalised coordinates

\(\mathbf {x}\) :

Vector of physical degrees of freedom

\(\hat{\mathbf {x}}_i\) :

i-th eigenvector

\(()_0\) :

Constant part

\(()_1\) :

Referring to the initial configuration

\(()_2\) :

Referring to the altered configuration

\(()_A\) :

Referring to the discretisation of the aerodynamic model

\(()_\text {,droop}\) :

Referring to droop nose

\(()_{\text {S}}\) :

Referring to the discretisation of the structural model

\(\varDelta ()\) :

Deviation of variable

\(\dot{()}\) :

Derivative with respect to time

\(()_{,x}\) :

Derivative with respect to x

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Acknowledgements

Financial support has been provided by the German Research Foundation (Deutsche Forschungsgemeinschaft, DFG) in the framework of the Coordinated Research Centre SFB 880.

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Authors and Affiliations

  1. TU Braunschweig, Institute of Structural Analysis, Beethovenstr. 51, 38106, Brunswick, Germany

    Nora Neuert & Dieter Dinkler

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  1. Nora Neuert
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  2. Dieter Dinkler
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Correspondence to Nora Neuert.

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Neuert, N., Dinkler, D. Aeroelastic behaviour of a parameterised circulation-controlled wing. CEAS Aeronaut J 10, 955–964 (2019). https://doi.org/10.1007/s13272-018-0348-6

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