Adverse Yaw amplitude (Cnda)

[dany93]

Forked from #1364

Let's start by what I think should be the easiest.

Averse Yaw (Cnda)

Megginson	Roskam	c172p	c182s	PA28
-0.0504, -0.0216, -0.0786	-0.053	Megginson's values	+0.0216 to +0.0786	-0,0008676
				0.2892x(-0.0015)x2

The c172p Cnda is at -0.0216, the lowest value published bt Megginson and Roskam.
[EDIT 14 july 2021]
Sorry, it has Megginson's values.
[/EDIT]
The c182 is with positive coefficients, which is 'pro'-yaw, not adverse yaw.
The PA28 is at -0,0008676 (if I understood well), which practically comes down to 0. No adverse yaw can be observed.

I admit that the adverse yaw effect could be decreased (despite the values from reference publications), but I cannot believe that the C172 is the only light aircraft giving no adverse yaw at all.
Currently I have nothing else than Megginson and Roskam, apart from qualitative and subjective impressions by pilots (several who find the controls too sensitive, some who don't express negative remarks, others who are in strong disagreement even between each other).
My own observations on ultralights (a bit old and obviously qualitative) are that the adverse yaw is easily observable, and must be counteracted.
Adverse yaw counteracting is one of the main tasks of the rudder.

@okroth wrote in this message

CnDa: Megginson has -0.0504, -0.0216, -0.0786 for climb, cruise, approach... not sure why they differ, but the C172 does have adverse yaw...UIUC, Roskam, etc all use -0.053.

@okroth, can you confirm that you wrote?
@tigert, if you are still there, your opinion on the amplitude?
@algefaen?

Videos:
Coordinated turns
Airplane Rudders! Learn to FEEL coordination in the airplane and avoid stall spin flying accidents

@Octal450, @tonghuix
If possible please, could you make a video like the one above, showing the (absence of?) adverse yaw on your aircraft? The important is to start from stabilized leveled flight at a known airspeed, then (reasonably??) rotate the yoke only, with no rudder. And observe the temporarily opposite yaw movement prior to the desired one.
Oscillating side to side movements are interesting to observe too (see the video).
The dashboard objects can serve as references for angular evaluations.

[HHS81]

@dany93
Megginson uses all values from Roskams book. And of course they differ between climb, cruise, approach- Roskam names also the speeds, air pressure, beta angle, alpha angle, altitude etc. as well- which all influences the strength of yaw adverse.

to be short: low speeds, high angle attack and large aileron deflections makes a strong yaw adverse effect (https://slideplayer.com/slide/13344648/). So with cruise speed it should be very low- for at least the c182 I do know you don´t need any pedal input in turns.

The c182 is with positive coefficients, which is 'pro'-yaw, not adverse yaw.´
Just because it is positive, it doesn´t mean automatically ´pro yaw´

I recommend: https://www.youtube.com/watch?v=ewHL8-agBWI
gives you rpm, yoke movements and turn indicator reaction

You should also consider that the animation slip ball might not be correct in the c172p

[okroth]

Hi Dany, yes I can confirm the values. Roskam had given two values; one is the -0.053 from "ROSKAM, J., Methods for Estimating Stability and Control Derivatives of Conventional Subsonic Airplanes"  and the other triple is in "Roskam-Airplane Flight Dynamics and Automatic Flight Controls-Part 1-Appendix-B" from where Megginson obviously took them. NASA-CR975 gives CnDa = -0.0167 for a C182 based on theoretical computations. Regards, Oliver Am 07.07.21 um 16:23 schrieb dany93:

…

Forked from #1364 <#1364> Let's start by what I think should be the easiest. *Averse Yaw (Cnda)* Megginson Roskam c172p c182s PA28 -0.0504, -0.0216, -0.0786 -0.053 -0.0216 +0.0216 to +0.0786 -0,0008676 0.2892x(-0.0015)x2 The c172p Cnda is at -0.0216, the lowest value published bt Megginson and Roskam. The c182 is with positive coefficients, which is 'pro'-yaw, not adverse yaw. The PA28 is at -0,0008676 (if I understood well), which practically comes down to 0. No adverse yaw can be observed. I admit that the adverse yaw effect could be decreased (despite the values from reference publications), but I cannot believe that the C172 is the only light aircraft giving no adverse yaw at all. Currently I have nothing else than Megginson and Roskam, apart from qualitative and subjective impressions by pilots (some who don't express negative remarks, others who are in strong disagreement even between each other). My own observations on ultralights (a bit old and obviously qualitative) are that the adverse yaw is easily observable, and must be counteracted. Adverse yaw counteracting is one of the main tasks of the rudder. @okroth <https://github.com/okroth> wrote in this message <#1047 (comment)> CnDa: Megginson has -0.0504, -0.0216, -0.0786 for climb, cruise, approach... not sure why they differ, *but the C172 does have adverse yaw*...UIUC, Roskam, etc all use -0.053. @okroth <https://github.com/okroth>, can you confirm that you wrote? @tigert <https://github.com/tigert>, if you are still there, your opinion on the amplitude? @algefaen <https://github.com/algefaen>? *Videos*: Coordinated turns <https://www.youtube.com/watch?v=UV8xcm5xsuo> Airplane Rudders! Learn to FEEL coordination in the airplane and avoid stall spin flying accidents <https://www.youtube.com/watch?v=zdZ2Rwq86vA> @Octal450 <https://github.com/Octal450>, @tonghuix <https://github.com/tonghuix> If possible please, could you make a video like the one above, showing the (absence of?) adverse yaw on your aircraft? The important is to start from stabilized leveled flight at a known airspeed, then (reasonably??) rotate the yoke only, with no rudder. And observe the temporarily opposite yaw movement prior to the desired one. Oscillating side to side movements are interesting to observe too (see the video). The dashboard objects can serve as references for angular evaluations. — You are receiving this because you were mentioned. Reply to this email directly, view it on GitHub <#1378>, or unsubscribe <https://github.com/notifications/unsubscribe-auth/ACNSRMDKBD5MP4ETXHY4JIDTWRPOHANCNFSM476YZM4Q>.

[dany93]

So with cruise speed it should be very low- for at least the c182 I do know you don´t need any pedal input in turns.

Isn't it merely because we don't need much aileron deflection in cruise? I admit, at least partly because Cnda (per radian of aileron deflection) might also be lower. But still far from 0.

In Megginson's table (C182), -0.0216 is the value for cruise.

low speeds, high angle attack and large aileron deflections makes a strong yaw adverse effect

I'd like to observe this.

Anyway, the main question is: even knowing that Cnda depends on AoA and / or airspeed, what are the values to be entered? Even if Megginson values are for 'mean' conditions (not taking every parameter in account), why are they considered as wrong in all of our conditions?

On the video (I already had seen it), the adverse yaw is difficult to distinguish from the other movements.
Moreover, it seems to be a flight simulator, and hard to take a simulator as an accurate reference...

[dany93]

Hi Oliver,

Nice to meet you again, and see that you are still there.

Thank you for your response.

Dany

[okroth]

Hi, IMHO, the CnDa should be a more or less constant parameter NOT being dependent on AoA. Of course, in slow flight, we need larger aileron movements for the same roll rate change, but that should not change CnDa; we already have a larger delta-aileron. Roskam's values also are not a linear function of alpha: cruise:   alpha=0.0°  CnDa= -0.0216 approach: alpha=4.0°  CnDa= -0.0786 climb:    alpha=5.4°  CnDa= -0.0504 i.e. CnDa is larger in approach than in climb with smaller alpha, but smallest with alpha=0... Regards, Oliver Am 07.07.21 um 18:30 schrieb dany93:

…

Hi Oliver, Nice to meet you again, and see that you are still there. Thank you for your response. Dany — You are receiving this because you were mentioned. Reply to this email directly, view it on GitHub <#1378 (comment)>, or unsubscribe <https://github.com/notifications/unsubscribe-auth/ACNSRMB7TJZAJIUXTHQ4NFDTWR6IVANCNFSM476YZM4Q>.

[dany93]

Once more, Thank You @okroth.

Of course, in slow flight, we need larger aileron movements for the same
roll rate change, but that should not change CnDa; we already have a
larger delta-aileron.

Your response confirms my reasoning between high AoA and cruise AoA adverse yaw, as based on my current understanding.
The current Cnda for FG c172p (-0.0216) is in accordance with your set of values, at the lower value.

Dany

[wlbragg]

This subject is really hard to quantify. Part of my reluctance to get on board to make any changes is the subjectivity and the wide range of control equipment in use by users, the unknown variability in individual RL aircraft trim settings and flight control surface tuning, and the disparity between RL control feedback and simulated controls.
All these variables tend to lead me to the published numbers and make it up to the user to tune their aircraft to fly as they expect.

I know with my peddles, (which are not dialed in completely), I need only slight right rudder pressure. That is what I keep hearing from multiple real life pilots.
I can't even begin to compare controlling with a mouse or keyboard against the peddles.
I know this isn't scientific evidence based on numbers but I for one don't think dummying down a know published number is the correct way to handle this.

[dany93]

@HHS81 wrote

I´m not a fan of creating fdms just by "feeling". Rather more of numbers for given control inputs

I agree, and always tried to go this way as much as I could.

@HHS81 wrote

No one of us here has flight controls at home which simulates the forces created by the airflow, mechanic and everthing else involved, but is responsible for the "feel" of the aircraft. Or do you use hardware which has the same travel way like the real controls?
When I started to develope aircraft I was told that the fdm should work and be correct in use with hardware which simulates all this. Travel way, forces etc...

I agree too, and many seem forgetting this. Plus the return springs on our JS, which give a very different feeling than reality (without Force Feedback JS).

Concerning (rudder) sensitivity
Power Off Stalls
Watch the rudder movements at 1'10, 1'37, 2'05. Very small and accurate.
For those who say the aircraft is not controllable but only have rudder control by twisting a stick, imagine controlling with such an accuracy... Even with a potentiometer in good condition. Not considering the difficulty to move this twist without interfering with the other axes.

[okroth]

Hi,

@HHS81 <https://github.com/HHS81> wrote No one of us here has flight controls at home which simulates the forces created by the airflow, mechanic and everthing else involved, but is responsible for the "feel" of the aircraft. Or do you use hardware which has the same travel way like the real controls?

Ahem, I do. I am building a home-cockpit that has motors being driven by the hinge moments computed in the FDM. I inserted an extra force-feedback system into the plane's XML file. And yes, the controls do have the actual travel way. And the rudder pedals are real parts. Oliver

[Octal450]

@dany93 i agree with you:

Watch the rudder movements at 1'10, 1'37, 2'05. Very small and accurate.
For those who say the aircraft is not controllable but only have rudder control by twisting a stick, imagine controlling with such an accuracy... Even with a potentiometer in good condition. Not considering the difficulty to move this twist without interfering with the other axes.

People should not be whining about small movement. If you can't get small enough the sensitivty should be adjusted, not the plane. The plane's response should be realistic. A twist rudder is bad for flying GA as you can't keep a constant input without uncomfortable. Recommend you use something even like some cheap racing pedals work.

Kind Regards,
Josh

[Octal450]

The PA28 is at -0,0008676 (if I understood well), which practically comes down to 0. No adverse yaw can be observed.

You're right, its too low. Some typo perhaps, I will go through and re-checked it a bit. I need to do more calculation and testing later. (very sorry for slowly... health problems not much time for fgfs)

Kind Regards,
Josh

[wlbragg]

Get better Josh!

[Octal450]

Thank you @wlbragg I hope so.

@dany93 . Value updated. Try now.

Kind Regards,
Josh

[tonghuix]

Concerning (rudder) sensitivity
Power Off Stalls
Watch the rudder movements at 1'10, 1'37, 2'05. Very small and accurate.
For those who say the aircraft is not controllable but only have rudder control by twisting a stick, imagine controlling with such an accuracy... Even with a potentiometer in good condition. Not considering the difficulty to move this twist without interfering with the other axes.

For the video you provide, I have to say the rudder use in this perticular video is just a demostrate, it is record in steady flight situation, not a power-off stall situation. However, for the power off stall itself, requires some of rudder input indeed, of my experence about less than 1/4 of full range.

I agree to test it, we need a rudder peddle, rather than just twist a stick.

[dany93]

Hi Josh,

Get better, I hope as soon as possible. For fgfs, there is no rush.

[Octal450]

Ty guys... but prob will be a while, been battling this for years.

@dany93 new coeffs: https://sourceforge.net/p/flightgear/fgaddon/5900/

Now the effect is better. Please try it, it should be resolved but I admit I only could do minimal testing in a few configs (slowflight, cruise).
Fyi: I see the typo of rad vs deg, its fixed in 5901.

Kind Regards,
Josh

[dany93]

@tonghuix wrote

For the video you provide, I have to say the rudder use in this perticular video is just a demostrate, it is record in steady flight situation, not a power-off stall situation

It is given as a power-off stall. Moreover, they say

"once the power is reduced to idle"

But it was not the subject. My aim was to show the needed accuracy on the rudder pedals.

[dany93]

@Octal450
I downloaded (.zip) and tested your r5901 version.

Better. The adverse yaw effect is weak (IMO) but observable.
Your values (if I understand well, tell me otherwise):
Cnda factor (left + right)
alpha = 0 deg : -0.002047 x 2 = -0.0041 (/rd)
alpha = 8 deg : -0.002047 x 1.667 x2 = -0.0068 (/rd)

IMO, the adverse yaw effect is still low. Hard to observe by eye, possible by yaw-rate-degps. Maybe observable by some lag on the yaw movement prior to the expected one just after the yoke deviation (starting from wings in leveled flight, of course).
But if that's your choice, you are better placed than me. And that's your aircraft.

@okroth wrote in this message

NASA-CR975 gives CnDa = -0.0167 for a C182 based on theoretical
computations.

Your values give 25% to 41% of -0.0167.

I think I observe an noticeable effect after applying a factor 3 or 4 to your values.

If you wish, to make tests and tuning of this factor easier in flight, I've inserted a 'factor' in the properties, which can be changed in flight.
In PA28-main.xml,

        <!--DANY adverse yaw tests-->
        <controls>
            <flight>
                <dany-fact type="double">1.0</dany-fact>
            </flight>
        </controls>  

In pa28-aerodynamics.xml,
insert inside both products for Cnda_l and Cnda_r:
<property>/controls/flight/dany-fact</property> <!-- DANY -->

[Octal450]

Hi @dany93 I will continue to check it in various configs, what config you test at?

I found the real life the effect is not as strong as in your c172 model, so I guess it also depends on what you are using for comparison. The effect is also small enough that you can comfortably fly the plane without rudder input if you HAVE to (jammed rudder or such) without the nose swinging about (I did simulated jammed surfaces training IRL)

Kind Regards,
Josh

[dany93]

Hi @Octal450

I use 160 or 180 hp, in the default config (the first as downloaded) in general. Not tested many configs, it was just ti give you a few indications.

I found the real life the effect is not as strong as in your c172 model, so I guess it also depends on what you are using for comparison

I obviously have the c172 in mind, consciously or not.
More objectively (despite qualitative) and real, I also have this video Coordinated turns.
From my memory (a bit old), flights on Ultralights, some of them with an instructor demonstrating me the adverse yaw.

I don't know what to think... the C182 has lower adverse yaw as calculated than C172
This message

NASA-CR975 gives CnDa = -0.0167 for a C182 based on theoretical computations.

Compared with C172

CnDa: Megginson has -0.0504, -0.0216, -0.0786 for climb, cruise, approach... not sure why they differ, but the C172 does have adverse yaw...UIUC, Roskam, etc all use -0.053.

Personally, I have nothing else than that I wrote just above in this message. I'd like accurate and constructive indications from reliable C172 pilots.

For the PA28, as you do your tests consciously with this issue in mind, you are probably right.

[tonghuix]

More videos for you @dany93 .

https://www.youtube.com/watch?v=zdZ2Rwq86vA

https://www.youtube.com/watch?v=0L4oKP5xv-8

[okroth]

That's cool! especially the first video will allow to calibrate the CnDa: 70kts, 80° aileron and then measure the plane's reaction... If it is similar to the video, we are almost there. Oliver Am 15.07.21 um 02:47 schrieb Tong Hui:

…

More videos for you @dany93 <https://github.com/dany93> . https://www.youtube.com/watch?v=zdZ2Rwq86vA <https://www.youtube.com/watch?v=zdZ2Rwq86vA> https://www.youtube.com/watch?v=0L4oKP5xv-8 <https://www.youtube.com/watch?v=0L4oKP5xv-8> — You are receiving this because you were mentioned. Reply to this email directly, view it on GitHub <#1378 (comment)>, or unsubscribe <https://github.com/notifications/unsubscribe-auth/ACNSRMF7W4FFO2FVMQBJR5DTXYV2DANCNFSM476YZM4Q>.

[okroth]

Hi dany, one more thing: Cnp "Yaw moment from roll rate". It contributes to adverse yaw when a roll rate is established whereas CnDa immediately applies a yawing moment. This coefficient is not existing (=0) in the detailed C172 I Roskam's "Flight Dynamics and ... Appendix B" it is give to Climbing: -0.0649 Cruise: -0.0278 Approach: -0.0960 Regards, Oliver Am 14.07.21 um 12:15 schrieb dany93:

…

Hi @Octal450 <https://github.com/Octal450> I use 160 or 180 hp, in the default config (the first as downloaded) in general. Not tested many configs, it was just ti give you a few indications. I found the real life the effect is not as strong as in your c172 model, so I guess it also depends on what you are using for comparison I obviously have the c172 in mind, consciously or not. More objectively, I also have this video Coordinated turns <https://www.youtube.com/watch?v=UV8xcm5xsuo>. >From my memory (a bit old), flights on Ultralights. Also, the C182 has lower adverse yaw as calculated This message <#1378 (comment)> NASA-CR975 gives CnDa = -0.0167 for a C182 based on theoretical computations. Compared with C172 CnDa: Megginson has -0.0504, -0.0216, -0.0786 for climb, cruise, approach... not sure why they differ, but the C172 does have adverse yaw...UIUC, Roskam, etc all use -0.053. Personnaly, I have nothing else than that I wrote just above in this message. For the C182, as you do your tests consciously with this issue in mind, you are probably right. — You are receiving this because you were mentioned. Reply to this email directly, view it on GitHub <#1378 (comment)>, or unsubscribe <https://github.com/notifications/unsubscribe-auth/ACNSRMEOB625P57VV3P2ILTTXVPS5ANCNFSM476YZM4Q>.

[HHS81]

Hi dany, one more thing: Cnp "Yaw moment from roll rate". It contributes to adverse yaw when a roll rate is established whereas CnDa immediately applies a yawing moment. This coefficient is not existing (=0) in the detailed C172 I Roskam's "Flight Dynamics and ... Appendix B" it is give to Climbing: -0.0649 Cruise: -0.0278 Approach: -0.0960 Regards, Oliver

Please note: These are the values for the c182

For c172p it is for cruise : -.03
https://groups.google.com/g/sci.aeronautics/c/69ECYNDKIJA

[Octal450]

Hi @dany93
I checked again, and re-adjusted the values, they were a little low still in some conditions. Now I find it matches pretty close to what I experienced properly.

Kind Regards,
Josh

[tonghuix]

More C172 training flight video:
https://www.youtube.com/watch?v=mCVzjUaKe2Q

Note that, due to the mount point of the camera, the pitch angle in the picture is much more lower than actural pitch angle.

[dany93]

Thank you @tonghuix for your videos.
I already had seen two of them, but did not show them as references because the "dynamic" procedure is uneasy to reproduce and evaluate.
Your https://www.youtube.com/watch?v=mCVzjUaKe2Q : the only part where I observe adverse yaw is at 22:15. Right?

Thank you Oliver @okroth and @HHS81
@HHS81 wrote
(Cnp "Yaw moment from roll rate")

Please note: These are the values for the c182
For c172p it is for cruise : -.03

Close to Roskam at cruise (-0.0278). A question is: to set an AoA dependency or not?

I'm looking at all of this when I can, but I have currently other problems to solve at home.

[dany93]

I have added Cnp (yaw moment due to roll rate)
https://github.com/c172p-team/c172p/tree/Issue-1378

It adds to the aileron contribution, increasing the primary adverse yaw moment. Not negligible at all, it can even be greater than the one due to ailerons. Which is the best way to get even more complaints with the published coefficients.

        <function name="aero/coefficient/Cnp">
            <description>Yaw_moment_due_to_roll-rate</description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/bi2vel</property>
                <property>velocities/p-aero-rad_sec</property>
                <table>
                    <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                    <tableData>
                        0        -0.0278
                        0.070    -0.0960
                        0.094    -0.0649
                    </tableData>
                </table>
                <property>/controls/flight/adv-yaw-fact2</property> <!-- tuning factor for tests in flight -->              
            </product>
        </function>

I hope (I think) having chosen the right properties, with bi2vel, in the product. (@okroth please ?)
The table coefficients for Cnp are those of Megginson.

Please note: For Cnda and Cnp, I have inserted
/controls/flight/adv-yaw-fact1 (Cnda)
/controls/flight/adv-yaw-fact2 (Cnp)
to allow tuning of each effect, separately, in-sim ("Set" in the Properties).

After many tests, I have set each tuning factor at 0.1. Surprisingly low, even if they add to each other. I don't know if that's enough, please tell me if they can be slightly greater.. Despite my reluctance, it is equivalent to setting the coefficients far from those of the published tables. I hope this is not a way to apparently fix an issue by introducing another ill-tuned feature.

The easiest way to test it is by comparison from Coordinated turns (from 1:30).
Starting from leveled wings, the observation is easy enough, not too much user dependent.

Testing from this video (5:00 and 6:04) can be more tricky.
The "dynamic" way (large left and right yoke movements at 70 kts) can be very user dependent. You must revert the yoke before the expected yaw movement begins. Otherwise, you can observe a false increase for advert yaw, in fact due to the inertia from the normal yaw.
To convince yourself, cancel both factors: if you wait too long, you can easily have the impression of adverse yaw.
You must also limit your yoke travel to 80% (like the video). To be sure, I have limited my aileron JS factor to 0.8.

Please test it, tune the factors in-sim and make an agreement between all of you.

From my point of view, important points are:

• reach the stall AoA (stall, stall and spin, in steep turns included),
• crosswind landing, at least 15 kt: get, keep fuselage-axis alignment with runway axis.

[okroth]

Dany, the "bi2vel" factor is correct. Reference: Roskam "Airplane Flight Dynamics and Automatic Flight Controls-Part 1",  page 130. Regards, Oliver Am 20.07.21 um 16:26 schrieb dany93:

…

I have added *Cnp (yaw moment due to roll rate)* It adds to the aileron contribution, increasing the primary adverse yaw moment. Not negligible at all, it can even be greater than the one due to ailerons. Which is the best way to get even more complaints with the published coefficients. |<function name="aero/coefficient/Cnp"> <description>Yaw_moment_due_to_roll-rate</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <property>aero/bi2vel</property> <property>velocities/p-aero-rad_sec</property> <table> <independentVar lookup="row">aero/alpha-wing-rad</independentVar> <tableData> 0 -0.0278 0.070 -0.0960 0.094 -0.0649 </tableData> </table> <property>/controls/flight/adv-yaw-fact2</property> <!-- tuning factor for tests in flight --> </product> </function> | I hope (I think) having chosen the right properties, with bi2vel, in the product. ***@***.*** <https://github.com/okroth> please ?) The table coefficients for Cnp are those of Megginson. *Please note*: For Cnda and Cnp, I have inserted |/controls/flight/adv-yaw-fact1| (Cnda) |/controls/flight/adv-yaw-fact2| (Cnp) to allow tuning of each effect, separately, in-sim ("Set" in the Properties). After many tests, I have set each tuning factor at 0.1. Surprisingly low, even if they add to each other. Despite my reluctance, it is equivalent to setting the coefficients far from those of the published tables. I hope this is not a way to apparently fix an issue by introducing another ill-tuned feature. The easiest way to test it is by comparison from Coordinated turns <https://www.youtube.com/watch?v=UV8xcm5xsuo> (from 1:30). Starting from leveled wings, the observation is easy enough, not too much user dependent. Testing from this video <https://www.youtube.com/watch?v=zdZ2Rwq86vA> (5:00 and 6:04) can be more tricky. The "dynamic" way (large left and right yoke movements at 70 kts) can be very user dependent. You must revert the yoke before the expected yaw movement begins. Otherwise, you can observe a false increase for advert yaw, in fact due to the inertia from the normal yaw. To convince yourself, cancel both factors: if you wait too long, you can easily have the impression of adverse yaw. You must also limit your yoke travel to 80% (like the video). To be sure, I have limited my aileron JS factor to 0.8. Please test it, tune the factors in-sim and make an agreement between all of you. — You are receiving this because you were mentioned. Reply to this email directly, view it on GitHub <#1378 (comment)>, or unsubscribe <https://github.com/notifications/unsubscribe-auth/ACNSRMG2C3B7U45CTDIJKWLTYWBPVANCNFSM476YZM4Q>.