DummyCatz

@BIGNEWY Hi, could you possibly take a look at the above comments. Basically two bugs: 1. 1-bar scan beam size not realistic 2. radar beam exceeding antenna tilt limit The simulation of a true round earth is not related.

I don't think the same thing is true for the Viper, considering the recent update/increase in roll rate specifically. Plus there's a flight tested roll rate graph of F-16 from MIL-STD 1797A, showing a max achievable of 223-226 deg/s. Is there any equivalent graph for the Hornet?

Hi, it's based on control quality guidance and a bit of common sense in the flight control system domain: 1. With reference to MIL-STD 1797A, the F-16 is rated Level 1 in control quality, and a well developed phugoid to such extent is a very unwanted characteristics, that could immediately lower the control quality score rated by pilots. 2. This unwanted characteristics, if exist IRL, should be recorded in the Flight Characteristics section of T.O. -1. 3. The AAR gain is designed to be flown from 0 to 400 knots airspeed, and in this region of airspeed, the pitch-rate response should be consistent. 4. This behavior does not exist in the previous version of DCS F-16, which exhibits a very well dampened pitch-rate response. Considering this is not on the update/bug fix list, we need explanation from ED on which DCS version exhibits the correct behavior.

Hi, I don't think the inertia coupling bug in the roll axis, and the dynamic stability bug in the pitch axis, are the same thing.

Hi, The Yaw Rate Limiter will activate when AOA > 35 deg, as well as AOA < -5 deg while airspeed < 170 kts, that the flaperon and/or the rudder is automatically commanded to negate any yaw rate built-up. Current behavior: The rudder is deflected into the yaw. Expected behavior: The rudder should be deflected against the yaw. 16 Yaw Rate Limiter wrong rudder deflection.trk

Hi, Good job with the new FM/FLCS update. However I'm experiencing a greatly degraded dynamic stability when flying between 300 and 400 KCAS in AAR gains (AAR door open). This may apply to gear down too. Testing method: Open the AAR door and stay within 300 to 400 KCAS, apply a step input to make a pitch disruption. Observe the well developed phugoid. Expected behavior: The dynamic stability should at least be inline with that of airspeed < 300 KCAS. This degradation of dynamic stability is not recorded in the Flight Characteristics section in -1. F16 FLCS TO-LDG gains phugoid.trk

I'd like to mention that when AOA > 35 deg, a function called 'Yaw Rate Limiter' activates that commands the flaperon and rudder to negate any yaw rate built-up. (You can search for it in -1). Simply put, the flaperon will deflect into the yaw, and the rudder will deflect against the yaw. But it seems that currently in DCS, the rudder also deflects into the yaw, which seems to be another bug.

Large, simultaneous pitch and roll command and consecutive 360 degree maximum command rolls are prohibited according to -1. This is to avoid departures due to inertia roll coupling, which is a prominent issue with a relaxed static stability aircraft such as an F-16. Although the FLCS may have means to suppress it, such as reducing the AOA limit and roll rate limit, it may still happen when the inertia coupling caused pitch-up moment overwhelms the pitch-down moment generated by the horizontal stab. An example of inertia coupling caused departure in an F-16B: (This is not a spin.)