Sentence examples for flow aerofoil section from inspiring English sources

The aircraft had a redesigned, thinner, inverted gull wing of laminar flow aerofoil section.

The test cases are for a two-dimensional pitch-plunge aerofoil section and the AGARD 445.6 wing modified with a trailing-edge control surface.

Calculation of zero angle lift coefficient or zero lift angle can be done by crudely assuming that the zero lift angle for the aircraft equals the combination of zero lift angle of the aerofoil section and wing incidence setting.

Results obtained from the optimisation show that utilising the designing transonic wing aerofoil sections and plan form in combination with evolutionary techniques improve the aerodynamic efficiency.

The two main differences are their much higher rotational speed, which causes more fatigue cycles and higher yaw moments, and their operation at low Reynolds number, which means that thick aerofoil sections cannot be used near the root.

This paper explores the application of a robust Evolutionary Algorithm (EA) for aerofoil sections and wing plan form shape design and optimisation for the improvement of aerodynamic performance and the reduction of Radar Cross Section.

To ease the difficulty of mass production, the leading edge of the wing was straightened out and the ailerons' two aerofoil sections had smooth leading and trailing edges.

In the case of flow-aerofoil interaction, sound radiation results from the scattering of the kinetic energy in the steady jet flow by the moving aerofoil, while for the piston source problem, acoustic energy comes from part of the work done by the piston source, the other part being trapped in the potential motion near the source.

A piston source model is examined which is acoustically equivalent to the flow-aerofoil interaction problem; the sound radiation is identical in the two cases although the mechanisms of energy conversion are quite different.

The dynamic Reissner functional in conjunction with variational calculus has been employed to derive the equations of motion of pretwisted cantilever blades of asymmetric aerofoil cross section.

Car traffic would flow beneath the section spanning Wilshire.