Hi everybody,
So, I posted this a few weeks ago at
www.nederlandseluchtvaart.nl already. In the last two weeks, I've been terribly busy for school: we did a aircraft wiring harness design project but we misplanned the deadline... In the end, we saw we had only one week left instead of two... Ouch! But, we got there!
Anyway, I was talking about doing some preliminary work on the Flight Dynamics of my T.5. This involves struggling with the .air and .cfg files. To prevent making fundamental mistakes as I made with my D.21, I prepared myself a little better by reading Yves Guillaume's paper:
http://library.avsim.net/download.php?DLID=170811
Best starting point, and the point where it went wrong with the D.21, is the weight and balance section of the .cfg:
Code:
[WEIGHT_AND_BALANCE]
max_gross_weight=
empty_weight=
reference_datum_position=
empty_weight_CG_position=
empty_weight_pitch_MOI=
empty_weight_roll_MOI=
empty_weight_yaw_MOI=
empty_weight_coupled_MOI=
max_number_of_stations=
station_load.0=
To fill this properly, I needed the following table, as copied from the T.5 handbook:
(OK, I know, it's in Dutch AND Metric...)
The grey faces are to be included in the FSX empty weight baseline.
The maximum gross weight of the T.5 is 7650 kg. This is not corresponding to the table mentioned above but derived from another loading case. Basically, the bomb load differs and thereby increases the total weight by 400 kg. In the end, max_gross_weight will equal to 16856 lbs.
Next on is the empty weight. Microsoft defined it as
Total weight (in pounds) of the aircraft minus usable fuel, passengers, and cargo.
This would result in 5700.9 kg (TOTAAL GEWICHT - white and coloured faces).
Now we get to the reference coordinates. FSX has four sets of them:
- VMO: Visual Model Origin, origin of the 3D model and important for pitch, roll and yaw moments;
- reference_datum_position, used to locate all other points;
- Aerodynamic center wing, could be set in the .air, otherwise being calculated by FSX. Only influences pitch moments;
- Center of gravity.
To keep things simple, I decided to keep ref_datum, AC and VMO at the same location. To complete this action, I set the AC in the .air to (0,0,0).
In order to do this, I need to find the wing AC. Done with some calculations from the handbook. The handbook uses a plane, mid of the front spar, as a reference for all weight calculations. See figure below.
The leading edge of the Mean Aerodynamic Chord is at 0.395 m in front of the Vertical Plane. The MAC has a length of 3.385 m. AC is generally located at quarter chord: 0.395 - 0.25*3.385 = 0.45125 m behind the Vertical Plane. This is the AC and should therefore be the ref_datum and VMO. I set the ref_datum to (0,0,0) in the .cfg and translated my models to this point (tricky action... but done).
Now the CG location of the empty-weight state has to be entered. To this end, the total moment from the third column is divided by the empty weight (grey faces thingy taken into account). The resulting value is relative to the Vertical Plane, so subsequently corrected for the location relative to VMO. However, according to the manual the CG will shift backwards 1.1% due to landing gear retraction. This correction is taken along, resulting in a -0.022 ft longitudinal location of the CG with respect to VMO.
Moments of Inertion for pitch, roll, yaw and coupled. Microsoft states that the latter one generally equals 0, so I take that. If someone disagrees, please tell me.
However, according to Guillaume, FSX doesn't calculate the MOIs of the loaded states correctly, resulting in too low values. Guillaume recommends to use the zero fuel weight MOI instead of empty weight MOI.
That's it

Cheers!