High speed rotorcraft experience a region of reversed flow over the retreating blade of the rotor when operating at high advance ratios. This reverse flow region leads to various unfavorable effects including negative lift, increased drag, and a large pitching moment impulse. Additionally, due to the blade dynamics, the retreating blade is also at high risk of dynamic stall which further exacerbates the problems associated with unsteady blade loading. The effect of the sweep angle on a dynamically pitching rotor blade in reverse flow was explored experimentally. It was demonstrated that the introduction of a trailing edge reflex camber could reduce the adverse effects seen in this regime. A cantilevered, finite span NACA 63-218 blade with semi-aspect ratio sAR = 3 was examined at a Reynolds number Re_c = 1.78 × 10^5 both with and without a 10° trailing edge reflex camber. Three blades were tested: one with 20° forward sweep, one with 20°. backward sweep, and one with no sweep. Load measurements were taken while the blades underwent a periodic pitching cycle, and cycle averaged loads were extracted. It was found that the introduction of trailing edge camber reduced the cycle averaged hysteresis loop in most cases regardless of the blade’s sweep.