Sep 9, 1983 · highly swept wings - conical camber. The use of conical flow models for developing wing shapes received exten- sive attention in the 1950's. In the U.S., the conical camber wing concept was developed by Hall and co-workers at the …

The conical camber used was a simplification of the full NACA conical camber geometry described above. A comparison of the cambers is given. The report contains tab data for the forces and moments at both sub- and supersonic Mach numbers.

Conical camber means the camber line is not defined by a traditional camber line. Instead, it is defined by the intersection of a plane and the surface of a cone. The surface of the cone would be the new mean line of the wing (if you discarded any traditional airfoil camber and twist).

It has been studied both as a simple form of built-in conical camber, intended to recover some part of the axial force which is lost through separation at the leading edge of a plane slender wing; and as a variable-geometry device, intended to enlarge the range of lift coefficient over which an acceptable performance can be achieved. Many ...

In aeronautics and aeronautical engineering, camber is the asymmetry between the two acting surfaces of an airfoil, with the top surface of a wing (or correspondingly the front surface of a propeller blade) commonly being more convex (positive camber).

In an attempt to avoid flow separation at the leading edge of a thin delta wing with subsonic leading edges, an attachment line is prescribed there. This is done by requiring the load, as predicted by attached-flow theory, to vanish along the leading edge at the design lift coefficient.

Report presenting a theoretical and experimental study to determine the effectiveness of camber in reducing the drag due to lift resulting from pressure forces acting on low-aspect-ratio triangular and sweptback wings.

Conical Camber was used on the F-102, the F-106 and the B-58 Hustler, as well as the F-15 Charles Hall, inventor, looking at a WT model with conical camber.

Between 1907 and 1913 JW Dunne developed a conical leading-edge profile with much sharper camber increasing progressively outboard. Its purpose was to confer excellent stability and handling qualities to a swept wing, and it entirely succeeded.

The experimental studies of references 1 and 2 show that a modification of the surface shape desig- nated as conical camber resulted in large reductions in the drag due to lift values of such wings. The data also showed, however, that at super- sonic speeds an increase in the drag near zero lift resulted from the camber.