I do hear what you're saying, but Cl also varies with Angle of Attach, so there is still no definative value for it. The minimum speed at which an aircraft will theoretically be able to fly is that at which L=W at Clmax, which is to say stall speed (Vs). (The other limit on this may be physical-you may strike the tail before achieving that AofA). This is also refered to a Vmu (V minimun unstick)
I'm not sure what use you are intending to put these calculations to, but the fact is that performance figures are not arrived at in that way. Vs is determined in flight test, things like take-off speeds are calculated using factors of this data.
At no stage does a performance engineer say "The Cl is this or that, so I can achieve 110% of lift at this speed."
So in terms of what you are asking, drag the tail on the ground, and the aircraft will fly when it produces enough lift. This is what they actuall do in flight test!!
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