Hello,
My first post out there.
The climb gradient can be easily computed with
thrust to weight ratio - Cd/CL
Decreasing the weight will of course increase the climb gradient.
increasing the speed has several effects:
- decrease the thrust (negative effect)
- depending on where you are on the A/C polar, your lift to drag ratio may increase or decrease
- The critical case in which we usually compute climb gradients is the engine failure case : the higher the speed, the lower the need of rudder deflection, which will reduce the penalty in drag and improve climb performance.
It's all a matter of CL versus Cd curve.
Now for the A/C pitch, it's the sum of the AoA and climb gradient (or groundslope). You don't necessarily have a lower pitch at V2+10 since you may reach a higher climb gradient than at V2, for a very low decrease in AoA.
For the vertical speed, I won't learn anything to anybody by writing:
Vz=TAS*climb gradient.
Lets say you have your optimum climb gradient at 1.2Vs (wonderful, at V2), you won't have your best vertical speed at V2, you may find it at speeds between 1.3 to 1.5 Vs, depending on the A/C type (turboprop or turbojet, wing polar...)
all the best