On a kernel-function method for the calculation of the pressure distribution on a two-dimensional wing with harmonically oscillating control surface in subsonic flow

The method presented contains the numerical solution of the Possio integral equation: the pressure distrtbution is approximated by a series of loading functions of which the coefficients are solved by collocation. Three terms in the series are singular; their type and strength are derived by a consideration of the local flow near the hinge axis....

Application of a method for estimating experimental pressure distribution to an oscillating T-tail

The method proposed in NLR Report TR F.250 to estimate experimental pressure distributions from theory and from measured distributions for one vibration mode, has been applied to a T-tail configuration at low speeds. The results indicate that also in this case the method may be used successfully.

On the use of the method of matching asymptotic expansions in two-dimensional unsteady transonic

The use of the method of matching asymptotic expansions in two-dimensional unsteady transonic flow without shock waves of finite strength is discussed, Applying this method differential equations for the velocity potential are obtained, Particular attention is paid to the low frecpiency case. Basic formulae are derived for the calculation of...

Calculated results for oscillating T-tails in subsonic flow and comparison with experiments

A calculation programme to determine pressure distributions on oscillating T-tails in subsonic flow is briefly described. Calculated results are given and compared with measured results for a number of T-tail configurations. The influence of reflection by wind tunnel walls and fuselage is discussed

Theoretical unsteady pressure distributions and aerodynamic derivatives for the Fokker F.28 T-tail windtunnel model (model no. 12)

Theoretical pressure distributions and aerodynamic derivatives are given for a Fokker F 28 T-tail model oscillating in a low speed windtunnel. A computer programme especially developed for T-tail configurations has been applied.

A method for estimating unsteady pressure distributions for arbitrary vibration modes from theory and from measured distributions for one single mode

A method is proposed to estimate for a lifting surface pressure distributions to be measured for arbitrary vibration modes by the aid of theory and measured distributions for one single mode. Its usefulness is demonstrated on hand of two swept wings of small aspect ratio oscillating in incompressible flow. Due to insensitivity to reduced...

Some comperative calculations with the lifting surface theory of Laschka for circular and elliptic wings oscillating in subsonic flow

The lifting surface theory of Laschka has been applied to circular and elliptic wings oscillating in subsonic flow. Comparisons have been made with results of more analytic procedures. The influence of the chordwise position of the collocation points has been investigated.