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A physically coupled mid-fidelity aeromechanical and aeroelastic analysis is used to investigate the effects for a compound coaxial rotorcraft rigid blade structural design in terms of the dimensionless parameter such as Lock number, advance ratio, and lift-offset. A rigid compound coaxial rotorcraft X2 technology demonstrator is represented by the comprehensive rotorcraft analysis CAMRAD II, where the physical components of the main rotor, pusher propeller, fuselage and empennage are analyzed using the generalized free wake and vortex theory. The aerodynamic coefficients are computed by MSES and DATCOM+, and rotor cross-section properties are designed using VABS. Three blade design candidates are created for different Lock number, and systematic trim analyses are conducted by the different lift-offset and advance ratio sweep. Results are presented on how each component load affects the vehicle trim state, and an investigation of the new design bounds for Lock number to define a rigid coaxial rotor.