This paper investigates design trends and performance trade-offs for a lift- and thrust-augmented asymmetric single main rotor helicopter. The goal is to match the payload and range of a conventional medium-lift utility helicopter, but with an increased cruise speed of 240 knots. This configuration is compared to a thrust-augmented single rotor with a wing and a thrust-augmented coaxial design. A multi-stage multi-fidelity design framework (HYDRA) was used to sweep over the entire design space to arrive at the best vehicle design. The framework first employs simple energy based equations to calculate rotor power and drag to eliminate infeasible designs. Feasibe designs are then resized using comprehensive analysis to predict rotor performance in high-speed flight. The latter step, while relatively slower, still executes within minutes and incorporates physics-based rotor performance models without apriori tuning of power factors and other coefficients. This study presents an approach to reconcile aspects of blade flap dynamics for performance and sizing. Using this methodology, it was found that for the asymmetric compound slowed-rotor helicopter cruising at 240 knots, a stiff hingeless rotor design is required to achieve rotor trim.