Hi AllWas wondering... As it is very difficult to get exact figures as they are in real life. Does anyone know if there is a test procedure to establish the flight performance of the simulator aircraft. Establishing the stall speeds would be easy I suppose but what about for example the optimum climb, cruise, rotate speed, approach etc;.I was thinking if you can set these fairly accurate to your simulated aircraft then it would be much better than using the real life figures on a simulated aircraft where they do not really apply.Hope that is clear enoughRegards Pete

Doesn't anyone know????? :(

Hello Pete,that is the whole purpose of Flight Dynamics modelling. It probably more complex that you might expect. All the main parameters for lift, drag and pitch can be programmed in to the flight model. Starting with Flight Manuals the performance can be derived and then modelled into the .cfg and .air files.You might need to familiarise yourself with aerodynamics theory and Herves site is a good place to start. Engine performance is also important except in gliders.What a/c do you want to model?Ian

Thanks Ian, that site you mentioned after a search around I found some very useful stuff.I wasn't modeling a plane. What I meant was if a model wasn't quite right in the figures (v speeds etc) then create your own set of figures for the models flight dynamics.thanks Regards Pete

Best rate of climb1. fly at 2000' msl2. initiate a climb, full power. Pitch the airplane up and use the yoke to maintain 110 KIAS during the climb. When the airpseed is stable, note the rate of climb3. go back to 2000'4. repeat climb, this time trim for 100 KIAS. Note rate of climb5. Continue this exercise in 10 knot increments until minimum controllable airspeedyou will have a log that looks like this (hypothetical data):speed rate of climb110 300100 50090 75080 100070 90060 600Best rate of climb is 1000 at 2000' 80 KIASYou can deduce the best angle of climb from these data by calculating the distance over the ground at various airspeeds assuming no-wind condition per 1000' of altitude using geometry. Given airspeed and rate of climb, use pythagorean theorm to solve for distance covered in a single minute, for example: KIAS rate of climb horizontal dist (ft) alt gained /nm/min ft / min covered in 1 minute horz dist 110 300 11000 0.03 100 500 9987 0.05 90 750 8969 0.08 80 1000 7937 0.12 70 900 6941 0.13 60 600 5969 0.10You can see the best rate of climb is 80 KIAS but the best angle of climb is 70 KIAS.You can see more at: http://www.dfrc.nasa.gov/Education/OnlineE...ht/nassawt.html

Thanks CindyThat is exactly what I was after.Regards Pete