Suggestion for database, data supply
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And google translation:
Yeah right Arty, it was translated by YOU, I always knew you were a Rooskie.:D
RAM22
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:munch:
Unless someone (who has a good understanding of how the exe interputes the data) does a full on AFM we are still hamstrung.
And even then a non F-16 AFM might not be possable.
Just my 20.5343 cents worth……Shad
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https://www.benchmarksims.org/forum/attachment.php?attachmentid=7231&stc=1&thumb=1&d=1329304660
To ensure good maneuverability characteristics of all admissible
range of angles of attack at subsonic flight speeds introduced a system of automatic control of the wing and flaperons socks at the signal angle of attack. With increasing angle of attack characteristics of the lateral stability and control remain satisfactory. up additional α
At speeds less than 400 km / h and α> 24 ° the plane has a low shear handling the derivation of the roll at speeds less than 400 km / h during the maneuvers along the border OΠP operation can throw over the angle of attack α additional
Therefore, the derivation of the bank to control the angle of attack, preventing excess
additional α
At angles of attack α> 28 ° up to the controllability of the aircraft does not stall aerodynamic buffeting occurs at angles of attack a = 9 ° -5 ° at M = 0.5-0,9 respectively. With increasing angle of attack increases the intensity of shaking and a Δα = 2 ° -3 ° is stabilized
The nature of the soft bumps in the entire range of angles of attack shaking piloting difficult and not a sign warning of the approach to the extra α can not serve
When disabled, and a failed control system toes wing flying is safe and has no features additional to α = 10 °
The behavior of the aircraft have been rejected on the toes of 30 ° (landing gear retracted, removed flaperons) has no singularities. Denial Management socks and flaperons at subsonic speeds does not cause the aircraft evolutions requiring the intervention of the pilot maximum increment of the congestion at the same time ΔΠχ ~ 0.5 The available angular speed of the roll by increasing the angle of attack decreases, but remains sufficient to additional α (20 ° / sec) The effectiveness of cross- control in horizontal flight provides the angular velocity of roll ωx> = 1,5 ° / sec
On takeoff and landing with the released of the wing and landing gear
Characteristics of stability and controllability of the aircraft without the suspension, and with all versions of missiles remain acceptable to the angle of attack |
a) For airplanes with no suspensions or SD ___
Μ 0.5 0.6 0.7 0.8 0.9 1.0
α π yes 24 23 22 20 19 18
Su FRA 1.85 1.7 1.58 1.45 1.3 1.2b) For airplanes with ABS Π up to 4000 kg, or HP
Μ 0.5 0.7 0,85
α ext 20 18 16
Suu additional 1.61 05.01 1.35The dependence of α marc-f (M, Η) (within the constraints πo α ext. Φmarc = 20 ° and Πy3) and subah = f (α M) are shown in Fig. 4 and 5
спасибо
Spashiba… lol -
@RAM22:
Yeah right Arty, it was translated by YOU, I always knew you were a Rooskie.:D
RAM22
Спасибо товарищу
lol -
NYET, COMRADE:D
You’re welcome.;)
RAM22
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Wow i think I understood some of that,
But lost you after “To ensure good maneuverability characteristics of all admissible”
Cheers……
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https://www.benchmarksims.org/forum/attachment.php?attachmentid=7232&d=1329304682
Guide pο aircraft flight manual of the Su-27SK
Restrictions:
green line α extra - for an airplane with no suspensions or SD.
blue line φmarc = -20
black line ny3marc AT T m = 21.4
red line α for the additional aircraft with PSIA to 4000 kg or with Hp
In Fig. 4. The maximum allowable angle of attack depending on the number of M.
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https://www.benchmarksims.org/forum/attachment.php?attachmentid=7233&stc=1&thumb=1&d=1329304697
In Fig. Five. Balancing the lift coefficient as a function of the angle of attack (flight test).
Арчер два JDAMS заголовком свой путь … LOL
So I’m at work now… I believe till I get home in 3 hours the update will be ready… Also I believe the Cobra maneuver must be just perfect…
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https://www.benchmarksims.org/forum/attachment.php?attachmentid=7228&d=1329304602
Figure 3 · Overload steady-bends, the plane with 2hR-73 * 2hR-27, with 50% residual fuel from the normal charging, the standard conditions of temperature, operating mode, the engine MAKSLMAL (for another mass nuf = n for a century. Sup. 20,000 )
MF
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The limitation curves are meaningless as long as FM is not close to real. With new FM + thrust should provide more accurate performance enevelope curve with 1g, this also means better acceleration model in level and climbing too. This should be the base of new FM. If aero force are far from real the limiters work that speed and AoA range where they sould not…
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https://www.benchmarksims.org/forum/showthread.php?8230-Suggestion-for-database-data-supply/page13
Figure 4, steady-state overload bends, the plane with two 2hR-73 xp-27, with 50% residual
Fuel from the normal charging, the standard conditions of temperature regime
raooty POLHy FORSAZh engines (for other mass nuF = nYou ust.vir., 20000)
MF
Done…
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Sorry m8 I forgot the thread and just responded to this one…
LOL we reinvented the wheel…Mav-jp is our man… Start licking him…
Please please…
We have f-16.
I’m sure M2k guys must be pushing for their FM… Also Mav is French so I’m sure he has something on the works… lol
F-18 is on the works if and a SU-27 will be close to real than we don’t want anything else… we can die in peace…
Of course Mav will die first after all those works… But I’m sure that he will give us the finger if u know what I mean… lol:D:D:D
Still a lot of work ahead…
BMS great simulator with a very good AMF F-16
if all else will be at the level just fine -
Translate
the main points in the graphs and tables
…
1 picture
Sustained turns (g)
Military thrust
Airplane configuration
2R-73+2R-27
Weight 20000kg (44092 lb)
for the weights are different from the above
Gnew=(Gon the chart20000)/New weight(kg)2 picture
the same
but the thrust = MAX (full afterburner)3 picture
limit of stability and controllability
for airplane with A-A missals or without
speed Mach number 0.5 0.6 0.7 0.8 0.9 1.0 2.0
indicator, of angle of attack (deg) 24 23 22 20 19 18 8with A-G (bombs, rocket launchers)
speed Mach number 0.6 0.7 0.85
indicator, of angle of attack (deg) 20 18 15the minimum speed horizontal flight (1g) - 200 kph (maximum fuel loading, with A-A missiles, believe me )
4 picture
At angles of attack α> 28 ° up to the stall, controllability of the aircraft is missingThe available angular velocity of the roll by increasing the angle of attack decreases, but remains sufficient to α (see previous table). (20 ° / sec). The effectiveness of lateral control in horizontal flight provides the angular velocity of roll ωh ≥ 1,5 ° / sec.
α доп. - angle of attack Limited by FLCS possible are exceeding, but there are additional features in the control
су доп. - LIFT COEFFICIENT (CL)
φмакс - maximum angle at which the stabilizer is deflected
Ny эмакс - the maximum operating load for the current weight -
@OSD:
I was just funny the current situation, when I uploaded the modified FM https://www.benchmarksims.org/forum/showthread.php?7259-Changes-in-the-flight-model nobody was looking, and charts on which changes were made, too, no one was looking.
could you upload your su27 FM again? the file link is gone.
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Ps = Thrust (lbs) - Drag
Sustained turn => Ps=0 => Thrust (lbs) = Drag
we have the CL(α,M), Trust(M, altitude)
how to find the Cd(α,M) will tell you MAV- JPThis is not the final version
it does not match the real 1:1, for obvious reasons
there are some features, even in the trajectory model, which are not reflected in the graphs in the Airplane Flight Manual
but I can not tell you about them
database contains incorrect weight suspensions and pylons as well as drag index
New version available FM… -
1 picture
Sustained turns (g)
Military thrust
Airplane configuration
2R-73+2R-27
Weight 20000kg (44092 lb)
for the weights are different from the above
Gnew=(Gon the chart20000)/New weight(kg)2 picture
the same
but the thrust = MAX (full afterburner)These are the only data that I can use for verification. I think FM is your work therefore you should do the comparsion.
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SA-5B test video is available on youtube.
The dat file is available in the uploaded directory, but here is the dircect link.
http://www.mediafire.com/?3iuguuntm8pc92h
RL engagement zones.
http://www.mediafire.com/?n6ff9wtnbn44ri9
Original data
_6172.94 # Weight of Missile (lbs)
3800 # Weight of propellant (lbs)5 # boost guide lead
5 # sustain guide lead
5 # terminal guide lead2 # Num MACH
0 4AXIAL FORCE COEFFICIENTS (CX)
0.35 # AXIAL MULTIPLIER
Mach 0.00
-1.12 -1.04 -0.96 -0.88 -0.8 -0.72
-0.64Mach 4.00
-1.55 -1.4 -1.3 -1.22 -1.15 -1.05
BURN TIME BREAKPOINTS
10 # Number of Time Breaks
#BURN TIMES
0 0.025 5.6 5.8
6 15 30 36 36.5
37ENGINE THRUST (LBS)
#THRUST
0 50000 50000 0
25500 21000 17500 12000 1000
0maxGTerminal 10.5
maxGNormal 10.5
MinEngagementRange 32800
MinEngagementAlt 6204_New data
**3600 # Weight of Missile (lbs)
5000 # Weight of propellant (lbs)2 # boost guide lead
2 # sustain guide lead
1 # terminal guide lead2 # Num MACH
0 6AXIAL FORCE COEFFICIENTS (CX)
0.60 # AXIAL MULTIPLIER
Mach 0.00
-1.12 -1.04 -0.96 -0.88 -0.8 -0.72
-0.64Mach 6.00
-2.55 -2.4 -2.3 -2.22 -2.15 -2.05
-1.9MISSILE MOTOR DATA
BURN TIME BREAKPOINTS
9 # Number of Time Breaks
#BURN TIMES
0 0.1 4.1 4.2 4.6
4.7 70 100 101ENGINE THRUST (LBS)
#THRUST
0 90000 90000 0 0
18500 7200 7200 0EngLocation -5.0 0.0 -0.1
maxGTerminal 10
maxGNormal 10
MinEngagementRange 55000
MinEngagementAlt 980** -
Great work molni, keep it up! I just installed your Sa-5.dat file.
Any way to fix Sa-3 bit?
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Yes, I have good news. I figured out what was the problem, it seems to me that I can increase the launch distance. The dat files of radar are the problem, the following lines.
Rangetoacuire [value]
Rangetoguide [value]I will post some long range engagement result of SA-2 and SA-5 where you can see the huge difference between old and tweaked models, + I try to set different high speed drag to SA-2 to get more close result about M2.0.
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Yes, I have good news. I figured out what was the problem, it seems to me that I can increase the launch distance. The dat files of radar are the problem, the following lines.
Rangetoacuire [value]
Rangetoguide [value]I will post some long range engagement result of SA-2 and SA-5 where you can see the huge difference between old and tweaked models, + I try to set different high speed drag to SA-2 to get more close result about M2.0.
That nice to hear, i think that thise fixes will make campaings way better because now red side has least working sam’s !