Chinook's likelihood of VRS is pretty high

[Ddg1500]

i the past, i though hind was pretty awful in VRS,  now my view has changed, chinook is a more VRS likely aircraft than hind, i VRS 5 times already.

and the throttle resposne is pretty wizardry too, when i was trying to approach and slow down, i feel that the aircraft is descending a little too much, so i add collective, but to my surprise, those "ought to be" sufficient add is "insuifficent" to reduce descent, it keeps droping down with some insidious shake, and then, i get into VRS and crashed.

Some of those VRS was happen with clean load and 60 percent fuel.

From what i see, this aircraft should be flown whith great care, that needs to reduce speed, and altitude pretty early on, and land with low altitude and short window of decent, otherwise, it would VRS.

Edited November 10 by Ddg1500

[RogueTalons]

I totally understand what you're saying, but based on my experience, I find the Mi-8 is much more prone to entering VRS compared to the CH-47.

With the Mi-8, I’ve encountered VRS much more frequently, even with relatively moderate descent rates. In contrast, I find that the Chinook is far more forgiving in this regard. As long as I keep the descent rate below 700 feet per minute, I’ve never had any major issues with VRS. I personally stick to a 1000 feet per minute limit, and as long as I stay within that, I can avoid the dreaded vortex ring state.

On the other hand, the Mi-8 seems to enter VRS much more easily, even at lower descent rates. It requires a lot more attention to manage speed and altitude carefully, as it seems to be much less forgiving.

[LuseKofte]

7 hours ago, RogueTalons said:

I find the Mi-8 is much more prone to entering VRS compared to the CH-47.

Might be the case , but I flown MI 8 so much that I recognise the early signs. I never go into that .But I flown CH 47 not that much and when I enter VRS state I have very little time to counter it.

[Av8tr]

The primary recovery method for a developing VRS in a Chinook is to apply lateral cyclic to fly out of the turbulent air, rather than forward cyclic, which can aggravate the issue by increasing the angle of incidence of the aft rotor system.

There is a phenomenon where the aft rotor head can enter a vortex ring state during rapid decelerations. This results in an abrupt nose-up attitude and a sinking feeling, which can lead to a hard landing if not quickly recovered.