Hello,
sorry I was'nt clear enough.
If you are at the same speed then you are totally right to say that the thrust is the same (for the little difference of ram recovery with inlet AoA, that's totally peanuts).
For the L/D ratio, I meant the lift to drag ratio, which gives for example the best glide speed.
What I wanted to say is that, even if you are at the same speed, the wing and the HTP are not at the same operating point (in terms of lift and drag coefficient), which may have an adverse effect. Of course, weight reduction will always win and the climb gradient will be better.
So, getting back to your initial question:
- No matter the weight, CAS=164KT : thrust is the same. No effect
- Weight is reduced : ++++ effect
- Lift to drag ratio is changed : may be positive or negative.
if you approach your speed for best vertical speed by staying at 164KT and reducing the weight, your climb gradient will be lower, and you will clear the 6,500m mic at a lower weight : I guess you then have a noisier aircraft.
So my advice is to find out the lift coefficient at which optimum climb gradient is get, then calculate the margin to stall speed, and fly at this speed, provided it is not lower than V2.
I hope this is helpful to your matter.
send me a private message if you need more details , or maybe a few graphs.