This related ASE answer may help -- "Does Lift equal Weight in a climb?". Note that a steady-state climb is associated with a smaller lift force than level flight, not a larger lift force. On the other hand, a loop is associated with a larger lift force than level flight.
If you increase the lift coefficient, you've increased the lift force -- if you keep airspeed constant. Since Mach is constant, and therefore airspeed is constant, it appears that your question is overly constrained. Not all your parameters can be met simultaneously if the flight path is to remain horizontal. In a particular aircraft in a particular configuration, only one value of the lift coefficient is consistent with horizontal flight at a particular indicated airspeed.
(Note-- actually we can decrease the indicated airspeed while holding the Mach constant, by choosing a higher cruising altitude. Since your question doesn't specify any particular altitude, this would appear to be a valid solution to your problem.)
On the other hand, if the altitude and Mach number are both constrained, constraining the indicated airspeed and giving "too much" lift at the optimal L/D ratio, and this is a design exercise, with the shape of the aircraft not yet "frozen", you could solve the "excess lift" problem by decreasing the wing area, allowing the aircraft to cruise at the optimal L/D ratio at the target airspeed and altitude.