Sea Sparrow(outdated) AIM-7 AIM-120B AIM120C R-77 MICA ( outdated) R-73 Super-530D ( updated by RAZBAM ) -- characteristic square (характеристическая площадь) //( missile surface, that*Cx = actual drag, remember the Sea sparrow = AIM-7 launched by ship ) 0.7 ( What ? ) 0.9 0.5 0.4 0.6 0.5 0.4 1.2, --Cx constraint parameters //( Drag coef ) 0.04 0.0125(too low )0.05 0.045 0.07 0.15 ( it is huge ! ) 0.05 0.04 ,--Cx_k0 Planck sx0 on a subsonic (M < < 1) //( pure subsonic drag ) 0.12 0.052(too low) 0.09 0.09 0.1 0.18 ( it is huge ! ) 0.12 0.08 ,--cx_k1 height of peak of wave crisis //( added drag near mach 1, lower is better ) 0.02 0.010 (too low) 0.02 0.02 0.02 0.02 0.02 0.05 ,--cx_k2 steepness front on approach to wave crisis //( higher is better ) 0.066 (too high) 0.002(too low) 0.018 0.016 0.03 0.043 0.062 0.04 ,--Cx_k3 Planck cx0 on Supersonic (M > > 1) //( pure supersonic drag ) 1.2 0.5(too low ) 1.5 1.2 2.0 2.0 1.2 2.0 ,--cx_k4 steepness recession for the wave crisis //( higher is better ) 1.2 1.2 1.5 1.5 1.2 1.2 1.0 1.0 ,--the coefficient of dump polar (proportional sqrt (M ^ 2-1)) //( what ? ) --Cy constraint parameters //( lift and induced drag (?) coef ) 1.0 1.0 0.8 0.7 0.9 1.0 0.9 0.4 ,--cy_k0 lath sy0 on the subsonic (M < < 1) 0.8 0.8 0.8 0.8 0.8 0.8 0.8 0.5 ,--Cy_k1 Planck cy0 on supersonic (M > > 1) 1.2 1.2 1.2 1.2 1.2 1.2 1.2 1.2 ,--cy_k2 steepness recession (front) behind the wave crisis 0.4 0.4 0.29 0.29 0.29 0.29 0.78 0.26 ,--7 Alfa_max maximum Balansirovachnyj angle, radians //( max alfa angle coef ) 0.0 0.0 0.0 0.0 0.0 0.0( while MICA does have thrust vectoring...) 5.0 0.0 ,--extra G by thrust vector Proportionnal navigation AIM-7 PN_coeffs = {2, -- Number of Entries 5000.0 ,1.0, -- Less 5 km to target Pn = 1 15000.0, 0.4}; -- Between 15 and 5 km to target, Pn smoothly changes from 0.4 to 1.0. Longer then 15 km Pn = 0.4. AIM-120B PN_coeffs = {3, -- Number of Entries 5000.0 ,1.0, -- Less 5 km to target Pn = 1 10000.0, 0.5, -- Between 10 and 5 km to target, Pn smoothly changes from 0.5 to 1.0. 15000.0, 0.2}; -- Between 15 and 10 km to target, Pn smoothly changes from 0.2 to 0.5. Longer then 15 km Pn = 0.2. AIM-120C PN_coeffs = {3, -- Number of Entries 5000.0 ,1.0, -- Less 5 km to target Pn = 1 10000.0, 0.5, -- Between 10 and 5 km to target, Pn smoothly changes from 0.5 to 1.0. 15000.0, 0.2}; -- Between 15 and 10 km to target, Pn smoothly changes from 0.2 to 0.5. Longer then 15 km Pn = 0.2. R-77 PN_coeffs = {3, -- Number of Entries 5000.0 ,1.0, -- Less 5 km to target Pn = 1 10000.0, 0.5, -- Between 10 and 5 km to target, Pn smoothly changes from 0.5 to 1.0. 15000.0, 0.2}; -- Between 15 and 10 km to target, Pn smoothly changes from 0.2 to 0.5. Longer then 15 km Pn = 0.2. if you want to read those data by yourself : DCSWolrd/Scripts/Database/Weapons/ Weapon data file ( need to be opened by C+ reader/editor ) exemple of FM data ( Google translated from Cubanace's Su-57 weapon Pack ) ModelData = { 58 , -- model params count 1.1,--characteristic square (characteristic square) --CX dependency settings 0.07,--Cx_k0 Planck sx0 on a subsonic (M < < 1) 0.08,--cx_k1 height of peak of wave crisis 0.02,--cx_k2 steepness front on approach to wave crisis 0.012,--Cx_k3 Planck cx0 on Supersonic (M > > 1) 2.5,--cx_k4 steepness recession for the wave crisis 1.2,--the coefficient of dump polar (proportional sqrt (M ^ 2-1)) --Cy constraint parameters 0.6,--cy_k0 lath sy0 on the subsonic (M < < 1) 0.3,--Cy_k1 Planck cy0 on supersonic (M > > 1) 1.2,--cy_k2 steepness recession (front) behind the wave crisis 0.2,--7 Alfa_max maximum Balansirovachnyj angle, radians 0.0,--angular velocity sozdavajmaja the moment of gas rudders --Engine data. Time, fuel flow, thrust. --T_statr t_b t_accel t_march t_inertial t_break t_end--Stage -1.0,-1.0, 6.0, 60.0, 0.0, 0.0, 1.0 e9,--time of stage, sec 0.0, 0.0, 30.0, 3.0, 0.0, 0.0, 0.0,--fuel flow rate in second, kg/sec (second fuel mass consumption kg/sec) 0.0, 0.0, 75000.0, 12000.0, 0.0, 0.0, 0.0,--Thrust, Newtons 1.0 E9,--self-elimination timer, Sec 200.0,--operating time of the power system, sec 0,--absolute height of the liquidation, M 2.5,--delay time of the control switch (flight maneuver, safety), sec 80000.0,--range to the target at the time of start, at the exceeding of which the rocket is carried out maneuver "Slide ", M 80000.0,--range to the target at which the manoeuvre "slide " ends and the rocket goes to a clean proportional navigation (must be greater than or equal to the previous parameter), M 0.15,--sine of the angle of elevation of the slide set path 30.0,--longitudinal acceleration of fuse firing 0.0,--speed module Soobshhajmyj catapult device, expelling charge, etc. 0.19,--Haraktristika systems of the SAU-rocket, factor filter of the second order K0 0.10,--Haraktristika system of SAU-rocket, Factor filter Second order K1 0.20,--Haraktristika systems of the SAU-rocket, the bandwidth of the control circuit 0.0, 0.0, 0.0, 0.0, 0.0, --DLZ. Data for the calculation of the starting distances (indication on the sight) 280000.0,--range angle 180 (towards) deg, n = 10000, V = 900km/h, M 115000.0,--range angle 0 (in Dogon) hail, n = 10000, V = 900km/h, M 145000.0,--range angle 180 deg, n = 1000, V = 900km/h, M 0.2,--reduction of allowed range of start-up at deviation of the vector of the speed of the carrier from the target line of sight. 0.7,--vertical plane. Slope of the allowed range of the start in the lower hemisphere. Reduced range when firing down. 2.4,--vertical plane. Slope of the allowed range of the start in the upper hemisphere. Increase the range when firing up. -3.0,--vertical plane. Bend angle of the allowed range, upper-lower hemisphere. 0.5,--change of the slope of the curve in the upper and lower hemispheres from the height of the carrier. 1.0, 1.0, 1.0, 0.2, 0.6, 1.4, -3.0, 0.5, }, }