Istochnikov
Costa Rica Space Systems' CEO
Hi
I have a question about how to develope an accurate aerodynamic model for my airplanes: I have the following data for... for example the Airbus A340-300:
An this model on SC3.dll
And i take off with some difficulty on 5000 meters. I have the data that an A340-600 fully loaded uses roughly 3000 meters (the lenght of the runway of Juan Santamaría Intl Airport) for taking off.
My question is: is possible to generate an accurate model of an aircraft in orbiter using the data mentioned on both [ CODE ] tags? And if answer is "yes", how can i implementate it both on SC3 or C++? (I shoud clarify that i'm an idiot on C++, so, please be patient with me
)
I have a question about how to develope an accurate aerodynamic model for my airplanes: I have the following data for... for example the Airbus A340-300:
Code:
Manufacturer AIRBUS
Type A340-
Model 300
Initial service date 1994
In service (ordered)
Africa 8(1)
Middle East/Asia/Pacific 54(10)
Europe & CIS 69(15)
North & South America 9(8)
Total aircraft 140(34)
Engine Manufacturer CFMI
Model / Type CFM-56-5C4
No. of engines 4
Static thrust (kN) 151.0
Operational Items:
Accomodation:
Max. seats (single class) 440
Two class seating 335
Three class seating 295
No. abreast 9
Hold volume (m³) 162.90
Volume per passenger 0.37
Mass (Weight) (kg):
Ramp 271900
Max. take-off 271000
Max. landing 190000
Zero-fuel 178000
Max. payload 48150
Max. fuel payload 33160
Design payload 28025
Design fuel load 113125
Operational empty 129850
Weight Ratios:
Ops empty/Max. T/O 0.479
Max. payload/Max. T/O 0.178
Max. fuel/Max. T/O 0.412
Max. landing/Max. T/O 0.701
Fuel (litres):
Standard 141500
Optional 148700
Manufacturer AIRBUS
Type A340-
Model 300
DIMENSIONS
Fuselage:
Length (m) 62.47
Height (m) 5.64
Width (m) 5.64
Finess Ratio 11.08
Wing:
Area (m²) 363.10
Span (m) 58.00
MAC (m) 7.26
Aspect Ratio 9.26
Taper Ratio 0.251
Average (t/c) %
1/4 Chord Sweep (º) 29.70
High Lift Devices:
Trailing Edge Flaps Type S2
Flap Span/Wing Span 0.665
Area (m2)
Leading Edge Flaps Type slats
Area (m²)
Vertical Tail:
Area (m²) 45.20
Height (m) 8.45
Aspect Ratio 1.58
Taper Ratio 0.350
1/4 Chord Sweep (º) 45.00
Tail Arm (m) 27.50
Sv/S 0.124
SvLv/Sb 0.059
Horizontal Tail:
Area (m²) 72.90
Span (m) 19.06
Aspect Ratio 4.98
Taper Ratio 0.360
1/4 Chord Sweep (º) 30.00
Tail Arm (m) 28.60
Sh/S 0.201
ShLh/Sc 0.791
Undercarriage:
Track (m) 10.70
Wheelbase (m) 25.40
Turning radius (m) 40.60
No. of wheels (nose;main) 2;10
Main Wheel diameter (m)
Main Wheel width (m)
Nacelle:
Length (m) 4.95
Max. width (m) 2.37
Spanwise location 0.312/0.672An this model on SC3.dll
Code:
[PARTICLESTREAM_1]
NAME=engine1
SRCSIZE=0.5
SRCRATE=700
V0=100.0
SRCSPREAD=0.01
LIFETIME=0.055
GROWTHRATE=1.9
ATMSLOWDOWN=1.0
LTYPE=DIFFUSE
LEVELMAP=LVL_PSQRT
LMIN=0
LMAX=2
ATMSMAP=ATM_PLOG
AMIN=1e-4
AMAX=1
[CONFIG]
MESHNAME="Commercial\airplanes\A340_IB" ;IB for IBERIA, LX for Swiss, LH for Lufthansa, TG for Thai...
SIZE=8
EMPTY_MASS=129850
FUEL_MASS=141150
MAIN_THRUST=622800
RETRO_THRUST=545000
ATTITUDE_THRUST=5e3
ISP=150000
TRIM=0.05
PMI=(15.5,22.1,7.7)
CW_Z_POS=0.09
CW_Z_NEG=0.09
CW_X=2.
CW_Y=1.4
CROSS_SECTION=(53.0,186.9,25.9)
COG=2.47
PITCH_MOMENT_SCALE=0.00005
BANK_MOMENT_SCALE=0.00005
ROT_DRAG=(1.2,0.9,2.0)
WING_ASPECT=0.7
WING_EFFECTIVENESS=2.5
LAND_PT1=(0,-8.521744,24.60485) ;(0,-8.59252,9) on Hi Poly Version
LAND_PT2=(-5,-8.521744,-.4498763) ;(-4,-8.59252,-5)
LAND_PT3=(5,-8.521744,-.4498763) ;(4,-8.59252,-5)
VISIBLE=0
CAMERA=(-5.388245,2.964641,28.24696)
MAIN_PSTREAM1=engine1
[SOUND]
MAIN_THRUST=Sound\Vessel\commercial\XA320_CFM56_fan.wav
HOVER_THRUST=Sound\Vessel\commercial\XA320_CFM56_Spool_2ORB.wav
RCS_THRUST_ATTACK=Sound\Vessel\roll.wav
RCS_THRUST_SUSTAIN=Sound\Vessel\roll.wav
[AERODYNAMICS]
; lift/drag attack point of the vertical airfoil
VAIRFOIL_ATTACK=(0,0,0)
; wing chord length of the vertical airfoil
VAIRFOIL_CHORD=7.26
; wing area of the vertical airfoil
VAIRFOIL_AREA=363.10
; wing aspect ratio of the vertical airfoil
VAIRFOIL_ASPECT=9.26
VAIRFOIL_EFFICIENCY=9.26
; lift/drag attack point of the horizontal airfoil
HAIRFOIL_ATTACK=(0,0,-4)
; wing chord length of the horizontal airfoil
HAIRFOIL_CHORD=20
; wing area of the horizontal airfoil
HAIRFOIL_AREA=45.20
; wing aspect ratio of the horizontal airfoil
HAIRFOIL_ASPECT=1.58
; surface area of aileron
AILERON_AREA=50
; lift change of aileron
AILERON_LIFT=3.3
; lift/drag attack point of left aileron (right aileron deduced by x -> -x
AILERON_ATTACK=(7,-0.5,-15)
; surface area of elevator
;AILERON_RIGHT_ANIM=3
; reference to animation sequence for the right aileron
;AILERON_LEFT_ANIM=2
; surface area of elevator
ELEVATOR_AREA=6.7
; lift change of elevator
ELEVATOR_LIFT=3.0
; lift/drag attack point of elevator
ELEVATOR_ATTACK=(0,0,-15)
; reference to animation sequence of elevator
;ELEVATOR_ANIM=1
; surface area of rudder
RUDDER_AREA=2
; lift change of rudder
RUDDER_LIFT=1.5
; lift/drag attack point of rudder
RUDDER_ATTACK=(0,3,-16)
; reference to animation sequence of rudder
;RUDDER_ANIM=4
; speed brake maximum drag change
;SPEEDBRAKE_DRAG=5
; speed brake drag attack point
;PEEDBRAKE_ATTACK=(0,7.5,-14);And i take off with some difficulty on 5000 meters. I have the data that an A340-600 fully loaded uses roughly 3000 meters (the lenght of the runway of Juan Santamaría Intl Airport) for taking off.
My question is: is possible to generate an accurate model of an aircraft in orbiter using the data mentioned on both [ CODE ] tags? And if answer is "yes", how can i implementate it both on SC3 or C++? (I shoud clarify that i'm an idiot on C++, so, please be patient with me
)
