14 August 2010 1.13 Aerospatiale/British Aerospace Concorde GPL (General Public License) http://www.gnu.org/licenses/gpl.html Nose gear is longer. Air intake effect, which allows more drag at Mach 1.3-2.0. Full tanks at maximum takeoff load. Tanks with dissymmetry. Landing pitch is 10 deg (maximum landing load) and ground effect. Climb pitch at 10 deg (maximum landing load). Climb Mach 0.95 to 1.7 in 10 minutes. Weaker supersonic lift Can reach Mach 2.0, below the VMO. Inside of center of gravity corridor. Shift of center of pressure. London - New York : lands below max landing weight (aloft westerly at 39 kt). Gear height adjusted by 3D model, supposed accurate. Pushback. Model uses flaps as nose. Cross feed by additional tanks : engine may run out of fuel above X 3 speed-up. Without an additional PID, above Mach 1, autopilot heading hold would lock with a right roll. Air intake failure only on the 4 engines at once. Ground idle only on the 4 engines at once. This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or restricted data. If this model has been validated at all, it would be only to the extent that it seems to "fly right", and that it possibly complies with published, publicly known, performance data (maximum speed, endurance, etc.). Thus, this model is meant for educational and entertainment purposes only. This simulation model is not endorsed by the manufacturer. This model is not to be sold. notation : "=>" denotes a final choice based on certain real values. Vlo (landing gear operation) : 270 kt. Vle (landing gear extended) : 270 kt. Vmc (minimum control speed with engine inoperative) Vmcl (approach) : 150 kt. Vmc (takeoff) : 132 kt. Vmcg (ground) : 116 kt. Datum : the datum for center of gravity computation is a vertical reference plane located 8.333 feet (2.540 m) forward of Fuselage Station X.A.0. A reference rigging point "C" is provided on the airframe 83.172 feet (25.351 m) aft of the datum at 13.66% C0. M.A.C. : the "reference root choord" (C0) is 90.748 feet (27.660 m) in length; its leading edge is located 70.771 feet (21.570 m) aft of the datum. Fuel tank capacity (at density 6.68 lb / US Gallon) : Tank Usable weight Total weight Arm (% MAC) ........................................................ 1 9348 9361 39.80 2 10176 10207 76.10 3 10176 10207 76.10 4 9348 9361 39.80 5 16032 16072 49.40 5A 4956 4963 74.80 6 25803 25889 66.70 7 16490 16525 64.70 7A 4956 4963 74.80 8 28590 28645 46.70 9 24710 24747 16.90 10 26597 26618 30.50 11 23192 23218 113.90 Systems 827 1021 69.43 ........................................................ Totals 211200 lb 211797 lb 56.23 - http://perso.wanadoo.fr/hsors/FS_Soft/FAQ-FS2K2-Decode_Forum.txt/ Ron Freimuth (for MSFS) : TYPE OF AIRCRAFT - ROLL,Rx PITCH,Ry YAW,Rz Single Low Wing .248 .338 .393 Single High Wing(C182R) .242 .397 .393 Light Twin .373 .269 .461 Biz Jet, Light .293 .312 .420 Biz Jet, Heavy .370 .356 .503 Twin Turbo- Prop .235 .363 .416 Jet Airliner 4 eng. .322 .339 .464 Jet Airliner 3 aft eng .249 .375 .452 Jet Airliner 2 eng wing .246 .382 .456 Prop Airliner 4 eng .322 .324 .456 Prop Airliner 2 eng .308 .345 .497 Jet Fighter .266 .346 .400 Prop Fighter 1 eng .268 .360 .420 Prop Fighter 2 eng .330 .299 .447 Prop Bomber 2 eng .270 .320 .410 Prop Bomber 4 eng .316 .320 .376 Concorde Delta Wing .255 .380 .390 (added, Ron Freimuth) Note: Delta Wing adds more to Pitch MoI due to Long Root Chord. Note: Yaw MoI ~ Pitch MoI + Roll MoI or a bit less. ... Estimate Aircraft Moments of Inertia - from Jan Roskam ... Roll Ixx = (W/g)*(Rx*b/2)^2 Pitch Iyy = (W/g)*(Ry*d/2)^2 Yaw Izz = (W/g)*(Rz*e/2)^2 Roll-Yaw Ixz less than or equal to 0.02 Iz, often 0.0 (added, Ron Freimuth) g = 32.174 ft/s^2 W = gross wt. lb b = span ft d = length ft e = (b+d)/2 Max TO - 408,000 lb No Fuel - 197,768 lb Length - 204.5 ft (.38*102)^2 = 1502 Span - 84.25 ft (.253*42)^2 = 113(Span+Length)/2 - 144.8 ft (.39*72.4)^2 = 797 Width - 9.5 ft Empty Mass - 197,768/32.174 = 6,142 slugs Max Mass - 408,000/32.174 = 12,670 slugs .... Empty Pitch: 1502 * 6142 = 9,227,000, Max: 19,034,000 slug ft^2 Roll: 113 * 6142 = 694,000, Max: 1,432,000 Yaw: 797 * 6142 = 4,897,000, Max: 10,100,000 Pitch is about 9,300,000, Yaw is 4,900,000, Roll is 696,000. The moments of inertia had been changed, as an attempt to solve the autopilot roll. - http://www.concordesst.com/ : Length : overall 202'4", nose to cockpit 24'. Height : fuselage max external 10'10". Width : fuselage max external 9'5". Gear : main track 25'4". Wing : span 83 ft. 10 in., length (root chord) 90 ft. 9 in.. Area (sq. ft) : Wing 3856, Elevon (each side) 172.2, Tail 365, Rudder 112. Weight (lbs) : max take off 408000, zero fuel 203000, operating empty 173500, max payload 29500, max taxing 412000, max landing 245000. Fuel : max 26400 gallons. TABLE A : Fuel tanks tank liters kg (density 0.792) .................................................. Engines supplies 1 5300 4198 2 5770 4570 3 5770 4570 4 5300 4198 Main storages 5 9090 7200 6 14630 11587 7 9350 7405 8 16210 12838 Auxiliary 5A 2810 2225 7A 2810 2225 Transfer and reserve 9 14010 11096 10 15080 11943 11 13150 10415 .................................................. Totals 119280 l 94470 kg Note that 1 US gal = 3.7854 liters. Maximum operating altitude : 60000 ft. Range : 4500 miles (3900 NM). Speed : max operating Mach 2.04, average takeoff 250 mph (217 kt), average landing 185 mph (161 kt). AOA : min -5.5 deg (above Mach 1), max 16.5 deg. Vortex above the entire wing creates lift at low speed and high AOA. Ground effect at landing : downwash of the air betweeen the wing and the ground. Delta wing provides a great deal of lift at Mach speed, with very little drag. Flight systems (range up and down) : inner elevons 9 deg, middle and outer elevons 23.5 deg, rudder 30 deg. Actual travel limits are a little lower than these mechanical limits. Turbulence mode reduces the trim rate. Gear : - main gear : track 7 ft. 72 in., brakes. - nose : wheelbase to main gear 59 ft. 8 1/4 in., no brake, +/-60 deg steering angle. - tail : no brake. - up process takes 12 s : door opening 2 s, gear retract 8 s, door closing 8 s. Nose : - from UP : visor transit 0 deg 6-8 s. - nose transit 5 deg 4-6 s. - to DOWN : nose transit 12.5 deg 5.7 s. Max total temperature (TMO) : 127 degC (on nose). Max oil temperature : start and takeoff 125 degC, takeoff and 5 minutes transient 195 degC, continuous operation 190 degC, starting -35 degC, adavance above idle -20 degC. Mas oil pressure : continued operation 5 PSI, takeoff 10 PSI. Max fuel temperature : startup -40 degC, advance above idle -40 degC, continued operation 50 degC. - http://www.alpa.org/alpa/DesktopModules/ViewDocument.aspx?DocumentID=814 : Mass gross weight : takeoff lasts 45 s, V1 165 kt, VR 195 kt, V2 220. Initial pitch at rotation is 13.5 deg. Cockpit is very noisy until nose is streamlined. Climb rate is slowly increased from 1500 to 3000 ft/s. Best lift-over-drag ratio over 300 kt. At takeoff, center of gravity is 51-52%, 58% at Mach 2.04. At Mach 1.3, inlet-guide ramps lower to slow down the intake air. At Mach 1.7 the afterburners are turned off, and the non-bypass engines are able to increase to Mach 2.04 (1150 kt) with about half the fuel flow. At cruise speed, the air entering the engines is reduced by intake ramps to 500 kt. This drop in intakes provides 45% of thrust, the engines 50%, and the convergent/divergent effect of the nozzle and stowed thrust reversers, 5%. At Mach 2.04, fuel flow is 45200 lb/h. Heathrow to Kennedy : 3h50. VREF is 162 kt at 275000 lb. - http://www.concorde-jet.com/ : Nose : O deg visor up supersonic, 0 deg visor down subsonic, 5 deg takeoff/subsonic, and 12.5 deg approach/landing/taxi. Takeoff : 175 kt, in 24 s, 1700-2100 ft/minute. Landing : 162 kt, 1500-1700 ft/minute. Subsonic cruise : Mach 0.93. Fuel : capacity 95680 kg, 20500 kg/h, 10000 at arrival. Aero reference point steps back of 2 m at Mach 2. - http://www.club-concorde.org/ : Min runway : takeoff 3600 m, landing : 2200 m.. Max wing loading : 488 kg/m2. Max climbing rate : 1525 m/minute. Takeoff speed : 214 kt. Landing speed : 130 kt, max 162 kt. Droop nose : 0.53 m. Front gear from nose (without droop nose) : 18.7 m. Main gear from front gear : 18.2 m. Distance of twin engine join : 11 m. Reheat provides 18% of additional thrust during take off. TABLE A corresponds to an effective filling at 95% of tanks (94% for tank 5). It is possible to surpass fuel gauges with 1660 additional liters. - http://www.aoe.vt.edu/~mason/Mason_f/ConfigAeroSupersonicNotes.pdf/ (Willian H. Mason) : CG (without CG (with Aerodynamic Mach fuel transfer) fuel transfer) center location .............................................................. 0.5 53.5 53.5 55.0 0.75 53.5 0.9 55.0 58.0 1.0 55.0 64.5 1.2 63.5 1.5 57.5 62.5 2.0 53.5 58.5 62.0 (all positions in % of aerodynamic chord C0, 90.748 feet). - http://www.titanic.com/story/159/Concorde/ : Runway : 11200 ft takeoff, 7300 ft landing. Max climb rate : 5000 ft/s. Range : 3550 nm supersonic, 2760 nm subsonic (Mach 0.95 FL300). Areas (sq ft) : wings (gross) 3856, elevons (total) 344.44, fin (excluding dorsal fin) 365, rudder 112. - http://www.dft.gov.uk/stellent/groups/dft_avsafety/documents/page/dft_avsafety_029047.hcsp/ (incident report, 13 june 2003) : The fuel tanks are arranged in 3 groups : the left main transfer group, the right main transfer and the trim transfer. The left and right main transfer groups store fuel in the wings and sections of the center fuselage, and both groups are comprised of 3 main tanks, which supply 2 collector tanks per group, from which the engines are fed. The collector tanks on the right main transfer group are tanks 3 and 4, which feed engines 3 and 4 respectively. The main fuel transfer system transfers fuel from the main transfer tanks to the collector tanks at a rate sufficiently high to ensure that the collectors tanks are always maintained in a near full condition. - http://www.nasa.gov/centers/dryden/pdf/87877main_H-913.pdf : The lift curve (delta wing) shifts downwards, temporarily at Mach 1.06, and completely near Mach 1.65. Differences of XB-70 : - cruise Mach 3 at 70,000 feet. - wider canards. - wingtips fold from 0 deg at Mach 0.75 to 65.70 deg at Mach 1.5 (transonic 25.30 deg). Pilot's eyepoint location, in aircraft's own coord system, FROM cg. X, Y, Z, in inches ORIGIN (0,0,0) is at NOSE. Center of gravity : - level at wing level : -1/4 of max external fuselage height (130 in.). - 51.7%, inside corridor of C0 (maximum takeoff load) => real C0 starts over front gear location (18.7 m). Aero refence point : - level at wing level : -1/8 of max external fuselage height (130 in.). - back of center of gravity reduces autopilot roll (step back at supersonic cruise). It has been found that 200 inches behind CG reduces AUTOPILOT ROLL. => real at Mach 2 is 62% of C0. Eye point location : length from nose to cockpit (24 ft), 1/4 of max external fuselage width (113 in.), 1/4 of max fuselage height (113 in.). Add ac_wingincidence : 1/20 of wing chord (C0). Htailarm : distance from CG to horizontal tail tip, none (5 ft). Vtailarm : distance from CG to vertical tail tip. 3856.0000 83.8300 90.7500 0.0000 5.0000 365.0000 5.0000 2.86 736.22 0.0000 -16.2500 288.0000 -28.2500 32.5000 0.0000 0.0000 0.0000 Center of gravity location, empty weight, in aircraft's own structural coord system. X, Y, Z, in inches; X is positive out the tail, Y positive out the right wing. 1432000.0000 19034000.0000 10100000.0000 0.0000 0.0000 0.0000 173500.0000 1299.4000 0.0000 -32.5000 29500 1299.4 0 -32.5 - => real nose (18.7 m = 736.2 in.), wing (18.7 m + 18.2 m = 1452.8 in.). - gear height determined by 3D model, supposed at scale. - tyre diameter of main gears, at 3/42 of the length between the gears (18.2 m) = 51.2 in. - adjust the front spring, to be horizontal at full load. 736.2000 0.0000 -178.5000 0.8000 0.5000 0.0200 40000.0000 40800.0000 60.0000 NONE 1 1427.2000 -152.0000 -158.5000 0.8000 0.5000 0.0200 408000.0000 81600.0000 0.0 LEFT 1 1478.4000 -152.0000 -158.5000 0.8000 0.5000 0.0200 408000.0000 81600.0000 0.0 LEFT 1 1427.2000 152.0000 -158.5000 0.8000 0.5000 0.0200 408000.0000 81600.0000 0.0 RIGHT 1 1478.4000 152.0000 -158.0000 0.8000 0.5000 0.0200 408000.0000 81600.0000 0.0 RIGHT 1 2081.0000 0.0000 20.0000 0.8000 0.5000 0.0200 122400.0000 40800.0000 0.0 NONE 1 additional contact points, for crash detection when gear retracted. 0.0000 0.0000 0.0000 0.8000 0.5000 0.0200 122400.0000 40800.0000 1825.2000 -503.0000 0.0000 0.8000 0.5000 0.0200 122400.0000 40800.0000 1825.2000 503.0000 0.0000 0.8000 0.5000 0.0200 122400.0000 40800.0000 2427.6000 0.0000 50.0000 0.8000 0.5000 0.0200 122400.0000 40800.0000 systems/NWS/engaged systems/NWS/hydraulics default is rudder pedal (flight). fcs/rudder-cmd-norm systems/NWS/engaged 0 1.0 1 0.0
fcs/rudder-pedal-norm - default is no wheel steering (flight). - default is hydraulics. - rudder steering at 10 deg. fcs/rudder-cmd-norm systems/NWS/engagedsystems/NWS/hydraulics 0.0 1.0 0 -0.0 -0.171 1 -0.0 -1.0
fcs/steer-cmd-norm /sim/model/pushback/target-speed-fps /sim/model/pushback/position-norm /sim/model/pushback/position-norm gt 0.95 gear/unit[0]/WOW == 1 gear/unit[0]/wheel-speed-fps lt 50 /sim/model/pushback/target-speed-fps -gear/unit[0]/wheel-speed-fps systems/pushback/speed-error /sim/model/pushback/kp /sim/model/pushback/ki /sim/model/pushback/kd systems/pushback/linked /sim/model/pushback/force systems/pushback/linked == 0 external_reactions/tractor/magnitude fcs/elevator-surface fcs/aileron-surface fcs/rudder-surface fcs/elevator-cmd-norm fcs/pitch-trim-cmd-norm -1.0000 1.0000 fcs/pitch-trim-sum fcs/elevator-surface fcs/elevator-surface 0.0175 => change -0.35/0.30 to -22.5/22.5 deg real. -22.5000 22.5000 fcs/elevator-pos-rad fcs/elevator-surface -1 1 fcs/elevator-pos-norm fcs/aileron-cmd-norm fcs/roll-trim-cmd-norm -1.0000 1.0000 fcs/roll-trim-sum fcs/aileron-surface fcs/aileron-surface 0.0175 => change 0.35 to 22.5 deg real. -22.5000 22.5000 fcs/left-aileron-pos-rad fcs/aileron-surface -1 1 fcs/left-aileron-pos-norm -fcs/aileron-surface 0.0175 => change 0.35 to 22.5 deg real. -22.5000 22.5000 fcs/right-aileron-pos-rad fcs/aileron-surface -1 1 fcs/right-aileron-pos-norm fcs/rudder-pedal-norm fcs/yaw-trim-cmd-norm -1.0000 1.0000 velocities/r-aero-rad_sec aero/qbar-psf 3.0000 0.0000 11.0000 2.0000
aero/beta-rad aero/qbar-psf 3.0000 0.0000 11.0000 0.0000
fcs/yaw-damper-beta fcs/yaw-damper-rate -0.2000 0.2000 fcs/yaw-damper-sum aero/qbar-psf 2.9900 0.0000 3.0000 1.0000
fcs/rudder-command-sum fcs/yaw-damper-final -1.0000 1.0000 fcs/rudder-sum fcs/rudder-surface fcs/rudder-surface 0.0175 => change 0.35 to 29 deg real. -29.0000 29.0000 fcs/rudder-pos-rad fcs/rudder-surface -1 1 fcs/rudder-pos-norm fcs/flap-cmd-norm changed 30 deg / 3 positions : use flaps as nose. 0.0000 0.0000 5.0000 12.5000 fcs/flap-pos-deg fcs/flap-pos-deg 0 12.5 0 1 fcs/flap-pos-norm gear/gear-cmd-norm => up in 12 s. 0.0000 1.0000 gear/gear-pos-norm fcs/speedbrake-cmd-norm 0.0000 1.0000 fcs/speedbrake-pos-norm - after FCS, which creates the intake command variable. - air intake on (supersonic) by default. - Engine center at 5/7 of length (2428 in.), -2/5 of fuselage height (130 in.). - Border aligned with main gear track (304 in. / 2). => real engine diameter is 1.65 m = (11 - 7.7) / 2. - Thruster center 3/4 of length (2428 in.), aligned with engines. fcs/ground-idle fcs/intake-subsonic-pos 1734.0000 -249.4000 -52.0000 0.0 0.0000 0.0000 13 1821.0000 -249.4000 -52.0000 0.0 0.0 0.0 1734.0000 -184.5000 -52.0000 0.0 0.0000 0.0000 14 1821.0000 -184.5000 -52.0000 0.0 0.0 0.0 1734.0000 184.5000 -52.0000 0.0 0.0000 0.0000 15 1821.0000 184.5000 -52.0000 0.0 0.0 0.0 1734.0000 249.4000 -52.0000 0.0 0.0000 0.0000 16 1821.0000 249.4000 -52.0000 0.0 0.0 0.0 The parameters are gear track, and tank 5 radius; to check against engine center. => Real length is arm, % of MAC (see table above) : real MAC (C0 1089 in.) starts at 18.7 m (736.2 in.). => Real half gear track is 7.7 m / 2 (151.6 in.). Configuration for take off with maximum weight : all tanks full, except tank 11 at 86%. Tank 1 : - 1/2 radius of tank 5. - align 3/4 of gear track. - => 39.80 % MAC. 1170.0000 -114.0000 -12.0000 50 9255.0100 9255.0100 59 Tank 2 : - 1/2 radius of tank 5. - align 1/2 of gear track. - near engine center. - => 76.10 % MAC. 1565.0000 -76.0000 -12.0000 50 10075.1300 10075.1300 59 Tank 3 : - 1/2 radius of tank 5. - align 1/2 of gear track. - near engine center. - => 76.10 % MAC. 1565.0000 76.0000 -12.0000 50 10075.1300 10075.1300 59 Tank 4 : - 1/2 radius of tank 5. - align 3/4 of gear track. - => 39.80 % MAC 1170.0000 114.0000 -12.0000 50 9255.0100 9255.0100 59 Tank 5 : - center + radius = gear position. - => 49.40 % MAC. 1274.0000 -152.0000 -12.0000 100 15873.2800 15873.2800 Tank 6 : - 3/2 radius of tank 5. - align 1/2 of gear track. - before engine center. - => 66.70 % MAC. 1463.0000 -76.0000 -12.0000 150 25544.9600 25544.9600 Tank 7 : - radius of tank 5. - before engine center. - => 64.70 % MAC. 1441.0000 152.0000 -12.0000 100 16325.2300 16325.2300 Tank 8 : - 3/2 radius of tank 5. - align 1/2 of gear track. - => 46.70 % MAC. 1245.0000 76.0000 -12.0000 150 28302.9500 28302.9500 Tank 9 : - 3/2 radius of tank 5. - centred on plane axis. - => 16.90 % MAC 920.0000 0.0000 -12.0000 150 24462.4900 24462.4900 Tank 10 : - 1/2 radius of tank 5. - centered on plane axis. - => 30.50 % MAC 1068.0000 0.0000 -12.0000 50 26329.8100 26329.8100 Tank 11 : - 1/2 radius of tank 5. - centered on plane axis. - => 113.90 % MAC 1977.0000 0.0000 -12.0000 50 22961.1400 19735.3100 Tank 5A : - radius of tank 5. - align 5/2 of gear track. - => 74.80 % MAC 1551.0000 -380.0000 -12.0000 100 4905.2900 4905.2900 Tank 7A : - radius of tank 5. - align 5/2 of gear track. - => 74.80 % MAC 1551.0000 380.0000 -12.0000 100 4905.2900 4905.2900 LP valve to emulate cross feed of engine : - position like the engine tank. - not empty, to avoid stop at launch. - can feed 75000 kg/h per engine (takeoff with reheat X 3 speed up) : 25000 x 3 / 3600 = 46 lb content, if supplied every 1 s from other tanks. 1170.0 -114.0 -12.0 46 46 1565.0 -76.0 -12.0 46 46 1565.0 76.0 -12.0 46 46 1170.0 114.0 -12.0 46 46 added : => real -5.5 to 16.5 deg. -5.5 16.5 Shift_of_center_of_pressure velocities/mach 0.5 0.550 0.9 0.580 1.0 0.645 1.2 0.635 1.5 0.625 2.0 0.620
Added : - additional lift on takeoff, otherwise tail touches the ground. - downwash of the air between the wing and the ground creates a cushion, making the landing smooth. Change_in_lift_due_to_ground_effect aero/h_b-mac-ft 0.0000 1.2000 0.1000 1.1500 0.1500 1.0900 0.2000 1.0200 1.1000 1.0000
Add Mach 0.0, 0.6, 1.1 and 1.4 : - increase (x1.2) climb drag to get 10 pitch; - increase (x1.2) landing drag to get 10 pitch and VREF 162 kt. - supersonic decreases drag (in front of the wave); - Mach 1.1 is end of transonic wall. - Mach 1.4 is supersonic cruise. Drag_at_zero_lift aero/qbar-psf metrics/Sw-sqft aero/alpha-radvelocities/mach 0.0000 0.6000 0.8000 1.1000 1.4000 -1.5700 1.5000 1.5000 1.5000 1.5000 1.5000 -0.2600 0.0408 0.0408 0.0340 0.0200 0.0120 0.0000 0.0204 0.0204 0.0170 0.0100 0.0060 0.2600 0.0408 0.0408 0.0340 0.0200 0.0120 1.5700 1.5000 1.5000 1.5000 1.5000 1.5000
Induced_drag aero/qbar-psf metrics/Sw-sqft aero/cl-squared 0.042 Add Mach 1.15, 1.3, 1.7 and 2.0 : - respect the thrust X 2.7 by air intakes. - supersonic decreases drag (in front of the wave). - Mach 1.8 adjusts climb rate : 0.015 -> 0.018. - Mach 2.0 adjusts consumption during supersonic cruise. Climb from Mach 0.95 to 1.7 in 10 minutes, adjusted by : - Mach 1.1 is end of transonic wall. - Mach 1.3 is start of effect of air intakes. - Mach 1.7 is end of reaheat. Drag_due_to_mach aero/qbar-psf metrics/Sw-sqft velocities/mach 0.0 0.000 0.79 0.000 1.1 0.023 1.15 0.020 1.3 0.019 1.7 0.016 1.8 0.013 2.0 0.010
nose drag. Drag_due_to_flaps aero/qbar-psf metrics/Sw-sqft fcs/flap-cmd-norm 0.0550 Drag_due_to_gear aero/qbar-psf metrics/Sw-sqft gear/gear-pos-norm 0.0110 0.0170 replaced by 0.0 : ctrl-B enables speedbrakes. Drag_due_to_speedbrakes aero/qbar-psf metrics/Sw-sqft fcs/speedbrake-pos-norm 0.0 Drag_due_to_sideslip aero/qbar-psf metrics/Sw-sqft aero/beta-rad -1.5700 1.2300 -0.2600 0.0500 0.0000 0.0000 0.2600 0.0500 1.5700 1.2300
- drag is always positiv. - divide by 10. Drag_due_to_Elevator_Deflection aero/qbar-psf metrics/Sw-sqft fcs/elevator-pos-norm 0.0055 Side_force_due_to_beta aero/qbar-psf metrics/Sw-sqft aero/beta-rad -1.0000 Add Mach 0.0 and 0.6 : - decrease (0 and x1/3 at 0 radian) landing lift to get 10 pitch; - decrease climb lift to get 10 pitch; - at low speed, lift is better (x0.75) at high AOA, because of vortex over the wing. Add Mach above 0.8 : - transonic (Mach 1.06) shifts the curve vertically (XB-70). - supersonic (above Mach 1.18) shifts the curve vertically (XB-70). - adjust consumption during supersonic cruise : drag increases with alpha. Lift_due_to_alpha aero/qbar-psf metrics/Sw-sqft aero/function/kCLge aero/alpha-radvelocities/mach 0.0 0.6 0.8 1.0 1.06 1.18 1.65 2.10 -0.20 -0.227 -0.227 -0.680 -0.680 -0.700 -0.680 -0.780 -0.880 0.00 0.000 0.067 0.200 0.200 0.180 0.200 0.100 0.000 0.23 0.900 0.900 1.200 1.200 1.180 1.200 1.100 1.000 0.60 0.200 0.200 0.600 0.600 0.580 0.600 0.500 0.400
changed 1.5 to 0.0 : used flaps as nose. Delta_Lift_due_to_flaps aero/qbar-psf metrics/Sw-sqft fcs/flap-cmd-norm 0.0000 -0.0800 replaced by 0.0 : ctrl-B enables speedbrakes. Delta_Lift_due_to_speedbrake aero/qbar-psf metrics/Sw-sqft fcs/speedbrake-pos-norm 0.0 Lift_due_to_Elevator_Deflection aero/qbar-psf metrics/Sw-sqft fcs/elevator-pos-rad 0.2000 Roll_moment_due_to_beta aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/beta-rad -0.1000 Roll_moment_due_to_roll_rate aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/bi2vel velocities/p-aero-rad_sec -0.4000 Roll_moment_due_to_yaw_rate aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/bi2vel velocities/r-aero-rad_sec 0.1500 Roll_moment_due_to_aileron aero/qbar-psf metrics/Sw-sqft metrics/bw-ft fcs/left-aileron-pos-rad velocities/mach 0.0000 0.1000 2.0000 0.0330
Roll_moment_due_to_rudder aero/qbar-psf metrics/Sw-sqft metrics/bw-ft fcs/rudder-pos-rad 0.0100 Pitch_moment_due_to_alpha aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft aero/alpha-rad -0.7000 Pitch_moment_due_to_elevator aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft fcs/elevator-pos-rad velocities/mach 0.0000 -1.3000 2.0000 -0.3250
Pitch_moment_due_to_pitch_rate aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft aero/ci2vel velocities/q-aero-rad_sec -21.0000 Pitch_moment_due_to_alpha_rate aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft aero/ci2vel aero/alphadot-rad_sec -4.0000 Yaw_moment_due_to_beta aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/beta-rad 0.1200 Yaw_moment_due_to_yaw_rate aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/bi2vel velocities/r-aero-rad_sec -0.1500 Yaw_moment_due_to_rudder aero/qbar-psf metrics/Sw-sqft metrics/bw-ft fcs/rudder-pos-rad -0.1000 Adverse_yaw aero/qbar-psf metrics/Sw-sqft metrics/bw-ft fcs/left-aileron-pos-rad 0.0000 736.2000 0.0000 -100.0000 1 0 0