Report of convergenceLoop: CeRAS-CSR-02

MTOM Convergence

Convergence successful
Postprocessing not successful
Needed time0.02 min
Number of iterations1

Key A/C Characteristics

MTOM [kg]:78619.9
OME [kg]:42154.3

Check tank volume

Max. Usable Fuel [kg]:32177.4
Loaded Fuel on Design Mission [kg]:19566.5

TLAR Unit Requirement Calc Rel. Change [%] Fulfilled Checked Recommendation
Balanced Field Length (BFL)
@ SL, MTOM, ISA+0-Conditions
m < 21220-10010
Landing distance (LDN)
@ MLM, SL, ISA+0
m < 23871353.28-43.3110
Approach speed (v_app) KCAS < 138128.745-6.7110
Initial Cruise Altitude (ICA)
after T/O @ MTOM, ISA+0
ft 3300033000010
Time-to-climb (TTC)
after T/O @ MTOM, ISA+0 (from 1500 ft to ICA)
min < 3515.83-54.7710
Max. operating (cruise) altitude
Climb with 100 ft/min @ ISA+0
ft > 3850035000
(38790.1)
0.7510
Max. ceiling
Climb with 50 ft/min @ ISA+0
ft -38945.9---
One-engine-out (OEI) net ceiling
Climb with 100 ft/min @ ISA+0
ft > 1500021589.843.9310
(Initial) Cruise Mach number - 0.780.78010
2nd (T/O) Segment Climb Grad. % > 2.42.409170.3810
Final (T/O) Segment Climb Grad. % > 1.22.40917100.7610
Approach Gradient (OEI) % 2.1 - - 10
Approach Gradient (AEO) % 3.2 - - 10

Top-Level Aircraft Requirements:

Parameter Unit Req. Value
Design range NM 2500
Design payload
[200 lb (=90.72 kg) per PAX]
kg 17000
Maximum payload kg 20000
(Initial) cruise Mach number - 0.78
Max. operating Mach number (MMO) kg 0.82
Max. operating speed (VMO) kg 350
Initial Cruise Altitude (ICA)
after T/O @ MTOM, ISA+0
ft 33000
Time-to-climb (TTC)
after T/O @ MTOM, ISA+0 (from 1500 ft to ICA)
min < 35
One-engine-out (OEI) net ceiling
Climb with 100 ft/min @ ISA+0
ft > 15000
Max. operating (cruise) altitude
Climb with 100 ft/min @ ISA+0
ft > 38500
Balanced Field Length (BFL)
@ SL, MTOM, ISA+0
m < 2122
Landing distance (LDN)
@ MLM, SL, ISA+0
m < 2387
Approach speed (v_app) KCAS < 138
Wing span limit m ≤ 36
ACN (flex B) - < 42

Key Aircraft Characteristics:

Parameter Symbol Unit Value
Design rangeRNM2500
Design passenger capacityPAX150
Cruise Mach numberMaCr-0.78
Wing loadingW/Skg/m2625.8
Thrust-to-weight ratioT/W-0.332
Maximum take-off massMTOMt78.6
Maximum landing massMLMt66.3
Operating mass emptyOMEt42.2
Manufacturer's mass emptyMMEt38.8
Maximum zero fuel massMZFMt62.2
Maximum fuel massMFMt32.2
Wing areaSrefm2125.624
Wing spanbm34.546
Mean aerodynamic chordMACm4.38782
Engine type-2 x V2527-A5
Sea-level static thrustSLSTlbf / kN28778 / 128.009


Material technology standard: aluminium wing and fuselage.
Iteration # MTOM OME xCG missionFuel
absrel absrel absrel absrel
Start values from Aircraft XML...
078619.942154.316.889419566.5
... after Setup Steps:
078619.942154.316.889419566.5
All outputs of the program 'convergenceLoop' were created with version 2.0.0