CRJ change notes

1) altered inertia values to calculated

2)pitch stability factor from -594687 to -400000

3) Pitch damper from 0 to 5000

4) center of lift from 202 to 50

5) spoiler pitch effect from 0 to 0.1

6) spoiler lift effect from 0 to -0.09

7) Aleron control factor from -589 to -380

8) Elevator control factor from -4183 to -2500

9) Reverse thrust to -17 from -7

10) oil temp factor from 91 to 26

11) TURBINE TEMP FACTOR FROM 256 TO 264

12) oIL PRESSURE FACTOR FROM 38 TO 43

13) Table 401 x values revised upwards by 0.03 (at zero crossing only)

14) fuel capacity from 1098 gal per tank to 851 gallons per tank

15) lift induced drag from 772 to 1772

16) fuel consumption vector from 400 to 436

17) wing longitudinal position from 17 to 27
