Another bug report, this time on the HMCS limits.
Sukhoi Su-27/30/33/35/37 Flanker series & Su-34 Fullback - History, Design, Performance & Dissection
Can you please provide a source or link ? Because manuals are usually not wrong, or I have never found a mistake in such important pilot manuals.
So in your sources, above 24 AoA there is no deterioration in lateral stability of the aircraft and above 28 AoA the aircraft is not laterally uncontrollable. Is that correct ?
The turn and the rising barrel of the Su-27UB at low altitude… Вираж и восходящая бочка Су-27 – смотреть видео онлайн в Моем Мире | Пётр Каракай (mail.ru)
Flight specifications of the Su-27 aircraft
Track stability is deteriorating, but not to zero.But the control of flaperons after 28 AoA is not possible
The manual says that
**At angles of attack α > 28° until stall, the aircraft is uncontrollable ( laterally).
It doesn’t specify what stops working, if flaperons or stabilizers or rudders but it literally says the aircraft is uncontrollable. That’s important.
Is there somewhere to get your sources or, would you at least send a picture, perhaps in a private message ?
TsAGI paper suggests that the success of the Cobra is the rapid attainment of the Cobra maneuver. Staying in a position of 30-40 degrees AoA creates large lateral instability and oscillations and causes departure. To Cobra you must surpass this and go to the point of flow separation over the wing with little lateral movements for the maneuver to be a success.
Now, to further your point… the Su-27 has been seen doing great lateral motions in its’ maneuvers and recovering with ease and full control. This would be a better example for comparison;
Here, the MiG-29M2 has a slight loss of track stability
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It is not my intention to argue, but to find the truth.
Sorry but the video is not of a Su 27, but a Su 35 with vectored nozzles, completely different digital FbW and a significantly different airframe. I am attaching the video and a picture of the aircraft for comparison.
The first Su 27, the one in WT and DCS, does not do this "Su 35 Super version of Cobra. “Classic Su 27” Cobra is a post stall maneuver. The point is that longitudinally the aircraft can get dynamically above 100 AoA (if the pilot has the balls to do it, that is with a very good pilot, because the safety constraints of AoA and G are turned off, the Cobra maneuver can kill weaker pilots).
But laterally, above 28AoA it is uncontrollable ( according to the manual for the SK version.
Su 27, the original one in the game and in DCS can do this :
Here performed by excellent test and demonstration pilots.
For those who don’t know, here performed by Sweden’s Drakken.
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so…did the you give up on fixing the flanker stupid speed bleed? or the r73 going crazy at low speeds and not tracking a target even with afterburner on(gripen) just cause he is flaring like a maniac
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It’s back to position because of inercia and because of coefficient drag to lift go sky hi above ~18 AoA and it’s not existent around ~30 AoA (basically 0 lift> movement Vector stay the same as inercia Vector) . It’s have nothing comon with control flying. Pilot is passenger above point where plane going into deep stall (according definition what some one post for you)
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I’m not reporting anything for war thunder anymore. I’ve shifted my focus towards other games.
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wise decision
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this Mig-29M2 and my picture shows a cobra Su-27
AoA 130,He came back thanks to pitch control, not inertia
In the SK manual there’re rolling and yawing moment coefficient derivatives with regard to sideslip angle (beta). Also known as lateral and directional static stability derivatives, denoted as Cl-beta (mx-beta) and Cn-beta (my-beta) respectively.
At M=0.2, Cn-beta is dropped to zero at 29° AOA, meaning there’s no yaw restoring moment available to reduce the sideslip. And Cl-beta is dropped to zero at 34° AOA, so no rolling moment can be generated with sideslip (by rudder).
If you compare them to the F-16:
These are two graphs of lateral and track stability, and we are talking about controllability. So mx- by delta flaperons at 28 degrees is equal to 0, and mx by delta rudder is not equal to 0 and the control moment is preserved
Yes, I’ve seen the graph of mx by delta flaperons and my by rudder some times back but couldn’t find it right now. It shows the mx-delta flaperons is zero at 28° AOA, and my-delta rudder at 30° AOA is about half of that at 10° AOA, but not at zero yet.
Yes, and the plane is still controlled by the roll using the rudder