Mehmet Velicangil <[EMAIL PROTECTED]> said: > can it be calculated. In one of the documents in the flight gear site I found that the rollout point which resembles an angle is approximately same with the maxroll which is taken 20 for Chessna and the rollout smooth point is approximately half of its maxroll angle. Are these ratios true for other aircraft or they are values found by certain handy equations that are dependant to the coefficients of the aircraft which is the main thing that I am wondering and want to learn about because I am trying to experiment with different aircraft by changing the values in the config files and try to make a realistic stuff while having fun and learning about aviation. >
The max roll values for the aircraft that I did were not derived by any scientific method. In some cases max roll was estimated from information available on the web (instructive or flight manual type data), estimated from web photos of aircraft in a bank, or just a wild guess. As far as rollout is concerned my main concern, where it varies, was simply to ensure that the aircraft did not overshoot the target in NAV mode. There isn't any rule AFAIK that it has to be equal to the roll, but you are welcome to experiment and submit any improvements or corrections. The aircraft that I have worked with as far as autopilot config is concerned are the 747, c310 and A4. Basically, the autopilot still requires more work. A little over a year ago autopilot was fixed to c172 requirements and not configurable. The configurability I added was mostly just a stopgap to get the it to operate without stalling and crashing the new higher performance aircraft. At this point I wouldn't read too much into what you see as far as those configurations are concerned :-) Best, Jim _______________________________________________ Flightgear-devel mailing list [EMAIL PROTECTED] http://mail.flightgear.org/mailman/listinfo/flightgear-devel
