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Fokker F70 Sample Analysis
This sample text output was compiled directly from the Piano model of the Fokker F70. Various reports are shown, in no particular order.
Welcome to Piano Version 3.6!
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calculating geometry/mass/balance ...
Fokker F70 option ____________________________
PAYLOAD 79. PAX = 15800.lb.
MTOW 84000. lb.
OEW 49984. lb. = 59.5% of mtow
FUEL-CAP. 3531. US.gal. Avail/Req=1.29
SPAN 91.9 feet
WING-AREA 1006. sq.feet trapezoidal
ENG.THRUST 13850. *2 lbf. reference fn*
13642. *2 lbf. available slst
W/S 83. p.s.f. trapezoidal
T/W 0.330 reference
0.325 available
______________________________________________
GEOMETRY REPORT
_______________
Wing Stabiliser Fin (excl.dorsal)
---- ---------- ---
Area, trapezoidal reference 1006.43 244.47 178.83 sq.feet
Area, piano gross 1008.99 244.47 178.83 sq.feet
Area, airbus gross 997.60 sq.feet
Area, boeing wimpress 1006.43 sq.feet
Area, esdu 1006.43 sq.feet
Area, exposed 821.77 244.47 178.83 sq.feet
Area, wetted 1676.69 497.20 363.44 sq.feet
Aspect Ratio, trapezoidal 8.40 4.50 1.00
Aspect Ratio, piano gross 8.38 4.50 1.00
Aspect Ratio, airbus gross 8.47
Aspect Ratio, boeing wimpress 8.40
Aspect Ratio, esdu 8.40
Span 91.95 33.17 13.37 feet
Sweepback at 1/4-chord 17.40 27.50 40.00 degrees
Taper Ratio (trapezoidal) 0.23 0.40 0.73
t/c at root 0.123 0.104 0.102
t/c at thickness break n/a
t/c at tip 0.096 0.104 0.102
Volume Coefficient (V-bar) 0.925 0.073
Mean Aerodynamic Chord 12.41 7.82 13.48 feet
Arm between MAC 1/4 chords 47.22 37.62 feet
Wing chord at tip 4.02 feet
Wing chord at planform break n/a feet
Wing chord at root (gross) 16.24 feet
Wing chord at c/line (gross) 18.34 feet
Wing chord at c/line (notional trapezoidal) 17.87 feet
Planform break location 0.000 (fraction of exposed semispan)
Thickness break location 0.000 (fraction of exposed semispan)
Wing location (station of extended leading edge at c/line):
35.78 feet (39.1 % of fuse.length)
Spar locations (fractions of local trapez.chord):
Wing root: 0.15, 0.65 Wing tip: 0.15, 0.65
Fuel capacity avail/reqrd = 1.293
------------- centresection is wet
Available: 3531.00 US.gal. (geometric capacity)
Required : 2731.03 US.gal. (at mtow & design payload)
Fuselage geometry
-----------------
fuselage max. width 10.83 feet
fuselage max. depth 10.83 feet
length, total fuselage 91.47 feet
length, front section 16.40 feet
length, mid section 35.37 feet
length, rear section 39.70 feet
wetted area, total fuselage 2587.85 sq.feet
wetted area, front section 416.91 sq.feet
wetted area, mid section 1202.05 sq.feet
wetted area, rear section 968.89 sq.feet
Nacelle geometry
----------------
nacelle length 16.08 feet
nacelle max. width 5.58 feet
nacelle max. depth 5.58 feet
wetted area per nac. 262.47 sq.feet
Overall dimensions
------------------
Span 91.95 feet
Overall aircraft length 101.25 feet
Height at top of fin 27.94 feet
Overall aircraft wetted area 5691.49 sq.feet
Design Limits
_____________
Design cruise point is Mach 0.77 at 32808.feet
Design dive Mach MD 0.82
Design cruise speed VC 327. KEAS
Design dive speed VD 384. KEAS
Limit load factor 3.16
Ultimate load factor 4.74
Cabin pressure differential 7.54 psi (limit)
Mass Report (in lb. and % of MTOW)
________________________________________
MTOW 84000.
OEW 49984. (59.5%)
MZFW 72000. (85.7%)
MLW 78999. (94.0%)
Mass Breakdown lb. % MTOW
________________________________________
wing group 8503. 10.12 %
(struct.box 6444.)
(flaps 1688.)
(spoilers 238.)
(ailerons 134.)
fuselage group 9527. 11.34 %
stabiliser 1095. 1.30 %
fin (incl.dorsal) 1003. 1.19 %
undercarriage 3247. 3.87 %
_____________________ _______ _______
basic structure total 23375. 27.83 %
powerplants total 7914. 9.42 %
furnishings 5608. 6.68 %
surface controls 1227. 1.46 %
fuel systems 562. 0.67 %
hydraulics 630. 0.75 %
electrics 1142. 1.36 %
avionics 647. 0.77 %
APU 573. 0.68 %
air conditioning 763. 0.91 %
misc. systems 2100. 2.50 %
_____________________ _______ _______
fixed equipment total 13252. 15.78 %
manufact. contingency 0. 0.00 %
_____________________ _______ _______
Manufact. Empty Mass 44541. 53.03 % = MEW
crew 1102. 1.31 %
operational items 4341. 5.17 %
_____________________ _______ _______
Operators Empty Mass 49984. 59.50 % = OEW
design payload 15800. 18.81 %
design fuel 18216. 21.69 %
_____________________ _______ _______
Maximum Takeoff Mass 84000. 100 % = MTOW
Calculating Design RangeÉÉDone.
RANGE REPORT
_____________
{Takeoff mass 84000.lb./ Fuel 18216.lb./ Payload 15800.lb.}
Range mode: fixed mach, step-up cruise, fixed climb sched.
Climb schedule: 250.kcas, 255.kcas, 0.650 mach
Cruise at Mach = 0.720 {FL 350}
ICA 35000.feet, 415.ktas, 242.kcas, CL=0.45, 2680.lbf./eng=MCR-9%
FCA 35000.feet, 415.ktas, 242.kcas, CL=0.39, 2486.lbf./eng=MCR-16%
Distance Time Fuel
(n.miles) (min.) (lb.)
_________ ______ _______
Climb 134. 24. 2573. {S.L to ICA}
Cruise 1158. 167. 9900. {ICA to ICA}
Descent 129. 23. 623. {ICA to S.L}
_________ ______ _______
Trip total 1420. 213. 13095.
Block total ========= 233. 13959.
Emissions: taxi,t/o climb cruise descent app,taxi total
(lb.NOx) 2.7 30.4 62.3 1.8 1.9 99.1
Manoeuvre allowances:
taxi-out 214. lb. {extra to t/o mass} 9.min.
takeoff 169. lb. 1.min.
approach 362. lb. 5.min.
taxi-in 119. lb. {taken from reserves} 5.min.
Diversion distance 200. n.miles
Diversion mach 0.648
Diversion altitude 26061. feet
Diversion fuel 2184. lb.
Holding time 45. minutes
Holding mach 0.258
Holding altitude 1500. feet
Holding fuel 2406. lb.
Contingency fuel 0. lb. {0.% of mission fuel}
Total Reserve fuel 4590. lb.
AERODYNAMIC DRAG REPORT at:
---------------------------
MACH 0.720
Altitude (pressure) 35000. feet
KTAS 415.0
KEAS 231.0
KCAS 242.2
Reynolds number 1.723 millions per foot
Delta-ISA +0. deg.C.
CL 0.440 based on:
Reference Area 1006.43 sq.feet (trapezoidal)
Drag Coefficients based on ref.area
-----------------------------------
Cd Zero-Lift 0.01922 (65.9 %)
Cd Lift-Induced 0.00867 (29.7 %)
Cd Compressibility 0.00115 ( 4.0 %)
Cd Trim 0.00013 ( 0.5 %)
Delta Cd (polar-mod) 0.00000 ( 0.0 %)
------- --------
Cd Total 0.02917 ( 100 %)
Aerodynamic Boundaries:
-----------------------
Divergence Mach 0.737 {at the given CL 0.440}
Initial Buffet Mach 0.861 {at the given CL 0.440}
Initial Buffet CL 0.881 {at the given Mach 0.720}
Zero-Lift Component Breakdown (Drag Areas,= Cd*S = D/q)
-----------------------------
Wing 5.901 sq.feet (30.5 %)
Winglets 0.000 sq.feet ( 0.0 %)
Fuselage & fairing 7.886 sq.feet (40.8 %)
Stabiliser 1.862 sq.feet ( 9.6 %)
Fin 1.291 sq.feet ( 6.7 %) (incl.dorsal)
Nacelles (total) 2.403 sq.feet (12.4 %)
User CdS Increment 0.000 sq.feet ( 0.0 %)
------- --------
Total Cd0*S 19.342 sq.feet ( 100 %)
Overall Lift / Drag Ratio = 15.08
=================================
Total Lift Force 80000. lbf.
Total Drag Force 5306. lbf. (2653.lbf. per engine)
Engine / Airframe Performance:
------------------------------
Total Fuel Flow at Thrust=Drag: 3665. lb/hr
Specific Fuel Consumption (SFC) 0.6908 lb/hr/lbf
Specific Air Range (SAR) 0.1132 nm/lb
Emissions Index, NOx 6.56 g/kg.
Available Total Thrust at MCR: 5901. lbf.
Available Total Thrust at MCL: 6394. lbf.
Instantaneous Performance Reserves at Weight=Lift:
RoC at MCR, constant Mach 0.720: 335. feet/min
RoC at MCR, constant 242.KCAS: 249. feet/min
RoC at MCL, constant Mach 0.720: 613. feet/min
RoC at MCL, constant 242.KCAS: 455. feet/min
Climb from 1500.feet to: 35000.feet
--------------------------------------------------
Time 22.72 minutes
Fuel burn 2461. lb.
Distance 129.8 n.miles
Initial mass 84000. lb.
Airspeed schedule 250.kcas, 255.kcas, 0.650 mach
Delta-ISA +0. deg.C.
NOx emissions 28.82 lb.
--------------------------------------------------
Climb details
Alt. Time Dist. Burn FN/eng R.o.C. NOx
(feet) (sec) (n.miles) (lb.) (lbf.) (f.p.m) (lb.)
1500. 0. 0.0 0. 7205. 2542. 0.0
2655. 28. 2.0 73. 7026. 2476. 1.1
3810. 56. 4.0 146. 6852. 2410. 2.1
4966. 85. 6.2 219. 6683. 2345. 3.1
6121. 115. 8.4 292. 6516. 2279. 4.1
7276. 146. 10.8 365. 6350. 2211. 5.2
8431. 178. 13.3 439. 6186. 2141. 6.2
9586. 211. 15.9 514. 6024. 2071. 7.1
10741. 249. 19.0 598. 5852. 1995. 8.3
11897. 284. 21.9 674. 5717. 1936. 9.2
13052. 320. 25.0 751. 5583. 1875. 10.2
14207. 358. 28.2 829. 5451. 1814. 11.2
15362. 397. 31.7 908. 5327. 1756. 12.2
16517. 437. 35.2 987. 5205. 1698. 13.2
17672. 479. 39.0 1067. 5084. 1638. 14.1
18828. 522. 43.0 1149. 4964. 1577. 15.1
19983. 567. 47.3 1232. 4845. 1515. 16.1
21138. 614. 51.8 1317. 4718. 1442. 17.1
22293. 663. 56.6 1404. 4596. 1368. 18.1
23448. 715. 61.8 1494. 4476. 1295. 19.1
24603. 770. 67.3 1587. 4363. 1224. 20.1
25759. 828. 73.4 1684. 4255. 1155. 21.2
26914. 890. 79.9 1784. 4150. 1087. 22.3
28069. 948. 86.0 1877. 4050. 1321. 23.3
29224. 1002. 91.8 1961. 3955. 1272. 24.1
30379. 1058. 97.8 2047. 3838. 1197. 25.0
31534. 1119. 104.3 2138. 3677. 1071. 25.9
32690. 1188. 111.5 2235. 3515. 941. 26.9
33845. 1268. 119.9 2341. 3354. 807. 27.8
35000. 1363. 129.8 2461. 3192. 668. 28.8
TAKEOFF PERFORMANCE {84000.lb., elevation 0.feet, ISA+0.deg.C.}
___________________
JAR25 Takeoff Field Length 4919. feet
115% Factored All-Eng.Dist. 4820. feet
Balanced Field Length 4919. feet
2nd Segment Climb Gradient 5.59 %
Takeoff CLmax 1.91 {trapezoidal ref.area}
Takeoff Vstall 114. keas
Takeoff Vfail 129. keas
Takeoff V2 136. keas
L/D at 2nd segment 12.54 {incl.windmill & asymm.}
Takeoff Wing Loading 83. p.s.f.{trap.W/S}
Takeoff Thrust/Weight 0.325 available static
LANDING PERFORMANCE {78999.lb., elevation 0.feet, ISA+0.deg.C.}
___________________
JAR25 Landing Field Length 4181. feet
Landing Distance (LFL*0.6) 2508. feet
Landing Ground Roll 1502. feet
Landing CLmax 2.43 {trapezoidal ref.area}
Landing Vstall 98. keas
Approach Speed 127. keas
Approach L/D 4.91 {gear down}
Iterating for Off-Design Range..Done.
RANGE REPORT
_____________
{Takeoff mass 75773.lb./ Fuel 9989.lb./ Payload 15800.lb.}
Range mode: fixed mach, step-up cruise, fixed climb sched.
Climb schedule: 250.kcas, 255.kcas, 0.650 mach
Cruise at Mach = 0.720 {FL 350}
ICA 35000.feet, 415.ktas, 242.kcas, CL=0.40, 2525.lbf./eng=MCR-14%
FCA 35000.feet, 415.ktas, 242.kcas, CL=0.39, 2484.lbf./eng=MCR-16%
Distance Time Fuel
(n.miles) (min.) (lb.)
_________ ______ _______
Climb 110. 19. 2149. {S.L to ICA}
Cruise 262. 38. 2179. {ICA to ICA}
Descent 127. 22. 617. {ICA to S.L}
_________ ______ _______
Trip total 500. 80. 4945.
Block total ========= 100. 5809.
Emissions: taxi,t/o climb cruise descent app,taxi total
(lb.NOx) 2.7 25.5 13.2 1.7 1.9 45.1
Prices, millions of U.S.$
________________________________
Airframe 11.63
Engines 3.08
Aircraft Delivery Price 14.71
________________________________
Costing method: aea-89-medium-range
Operating Costs U.S.$/trip % of total
______________________________________________
Depreciation 636. 11.79
Interest 494. 9.14
Insurance 43. 0.80
Flight Crew 845. 15.65
Cabin Crew 416. 7.70
Landing Fees 297. 5.50
Navigation 404. 7.49
Ground handling 717. 13.27
Fuel 650. 12.03 {0.750 $/US.gal.}
Airframe Maintenance 580. 10.75
Engines Maintenance 317. 5.87
________________________________________________
Total Ownership 1173. U.S.$ per trip
Total Cash 4225. U.S.$ per trip
Total D.O.C. 5399. U.S.$ per trip
________________________________________________
Utilization 1697 trips/year
Block time 1.71 hours
Block distance 500. n.miles
Block fuel 5777. lb.
Block fuel/seat 73. lb./seat
D.O.C./ block hour 3157. U.S.$/hr
D.O.C./ seat 68. U.S.$/seat
D.O.C./ seat-n.mile 0.13667 U.S.$/seat-n.mile
PAYLOAD-RANGE
_____________
Range mode: fixed mach, step-up
Max.payload / MTOW case
_______________________
Payload 22016. lb.
Range 651. n.miles
Fuel 12000. lb.
Cruise mach 0.720
Cruise alt. 35000. feet
Fuel volume limit / MTOW case (kinkpoint)
_____________________________
Payload 10464. lb.
Range 2109. n.miles
Fuel 23552. lb.
Cruise mach 0.720
Cruise alt. 35000. feet
Zero payload / TOW=OEW+max.fuel case
____________________________________
Payload zero
Range 2351. n.miles
TOW 73536. lb.
Fuel 23552. lb.
Cruise mach 0.720
Cruise alt. 35000. feet
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