Perhaps this? certainly not a linear 135# per 1mm TIR diameter increase, much more specific. Not being an engineer I'm not sure how it comapres to the current chart/grid being used but it may be worth considering.
Article 252 - 2011
Prescriptions Générales pour les
Voitures de Production (Groupe N), Voitures de Tourisme (Groupe A),
Voitures de Grand Tourisme (Groupe
General Prescriptions for
Production Cars (Group N), Touring Cars (Group A),
Grand Touring Cars (Group
3.3 Equivalence formula between reciprocating piston and
turbine engines
The formula is the following:
S(3.10 x R) - 7.63
C = ---------------------------
0.09625
S = High pressure nozzle area - expressed in square centimetres
by which is meant the area of the airflow at the exit from the stator
blades (or at the exit from the first stage if the stator has several
stages).
Measurement is done by taking the area between the fixed blades
of the high-pressure turbine first stage.
In cases where the first stage turbine stator blades are adjustable,
they must be opened to their greatest extent.
The area of the high-pressure nozzle is thus the product of the
height (expressed in cm) by the width (expressed in cm) and by the
number of blades.
R = The pressure ratio is the ratio of the compressor of the turbine
engine.
It is obtained by multiplying together the value for each stage of the
compressor, as indicated hereafter:
Subsonic axial compressor: 1.15 per stage
Trans-sonic axial compressor: 1.5 per stage
Radial compressor: 4.25 per stage.
Thus a compressor with one radial and six axial subsonic stages
will be designated to have a pressure ratio of:
4.25 x 1.15 x 1.15 x 1.15 x 1.15 x 1.15 x 1.15 or 4.25 x (1.15)6.
C = Equivalent cubic capacity for reciprocating piston engines in
cm3.
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Just had an idea/brain fart?!?!?
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