Abstract
An approximate method is developed which extends pressure distribution theories for wings of constant sweep to wings with curvilinear leading edges. Two cases are considered. In the first case of a predominantly subsonic leading edge, an analogy is made to a wing in conical flow. In the second case of a supersonic/subsonic leading edge, physical reasoning is used to approximate the flow regions on the wing with linesource solutions. An application is made to a wing of ogee planform, and comparisons with experimental data prove very favorable.
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