HazelNuts39
The response of the airplane changes. For example, in a steady state pull-up at 1.5 g, the pitch rate is 5.5 deg/sec at 100 kTAS, and 1.4 deg/sec at 400 kTAS.
Thanks HN, we are in the same game again.
Are those values real? Can we compute the values for the speeds for the times when SS was held NU and when later on SS was ND for some seconds?
Would that tell us, that during the period of unreliable low speed the pitch rate was at the high end, thus SS input caused rapid pitch change?
And when speeds became valid again at the initial higher speeds the pitch rate would have been smaller?
Could you work those values into one of your marvelous graphs from the respective time period?
HazelNuts39
Probably yes, but much more slowly. At 2:10:49 the pitch attitude was 6 degrees and the rate of climb 1100 fpm. Without SS input that RoC would have been maintained until the airplane stalled.
I see that point, but the normal acceleration (smoothed) was below 1g 13 seconds later and stayed below 1 g for over 1 minute. throughout the timeframe, the THS was moving. If the pull would have increased the travel rate, shouldn´t the normal acceleration then be above 1 g?