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My best current explanation: on a reverse delta wing, stability similar to a normal delta wing is achieved, caused by a differential in skin drag on the 2 sides of the wing. When the wing changes its position on the yaw axis without changing its direction of motion for example if the wing rotated clockwise from a birds eye view, the left side of the wing would have a larger distance for the air passing over it for travel, creating a higher amount of skin drag on that side of the wing and therefore moving the wing back to equilibrium on the yaw axis, this could be optimised by changing the surface of the wing to something that increases skin drag whilst you could have a thinner airfoil so to decrease the overall increase in drag (the thinner airfoil shouldn’t affect the skin drag, it is purely there to decrease the drag generated when the air immediately hits the airfoil). This stability works in effectively the opposite way that a normal delta wing has stability but unlike how a normal delta wing would decrease skin drag when the yaw axis changes, having a small negative effect on its stability, a reverse delta wing would not be affected by the immediate drag from a stability point of view as the front of the wing would be non swept. This wing could be used for super sonic aircraft if you sweep the front surface of the wing Backwards as long as the angle that the front edge is swept is less than the angle that the rear surface of the wing is swept forward, (the steeper the angle on the rear surface the greater the stability). This is all theoretical and I haven’t proofed any of this yet, but I do think that the idea at least has some merit to it and I will be making an RC plane that attempts to prove this in the future. Please send this and the video included in thus email to anyone that you think would know what I’m talking about and would know if it has already been discovered/proven or disproven.