Northwest Airlines DC-10-30 N233NW c/n 46640 at Schiphol, December 1997 © bvdz
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weight and performance calculations for the McDonnell Douglas DC-10-30
Northwest Airlines DC-10-30 N233NW c/n 46640 at Schiphol, December 1997 © bvdz
KLM DC-10-30 PH-DTA c/n 46550 “Johan Sebastiaan Bach”
McDonnell Douglas DC-10-30
role : wide-body airliner
importance : ****
first flight : 21 July 1972 operational : November 1972
country : United States of America
production : 163 aircraft at Long Beach
general information :
The DC-10-30 has a longer range and was a good alternative for many airlines on long-haul flights for which the 747 was too large.
The -30 was also offered as a convertible (-30CF) and as a cargo aircraft (-30F). The -30CF made the 1st flight on 28 February 1973 and in April 1973 the 1st was delivered. The -30 was the best-selling version. In 1988, production of the DC-10 was discontinued. The DC-10-30 has a larger wingspan and a slightly longer fuselage. MTOW is much higher than the DC-10-10. KLM and Swissair were the launch customers and were the first to take it into service. KLM ordered 5 aircraft, the PH-DTA, DTB, DTC, DTD and DTL, which were given names of composers. They were delivered between 15 March 1974 and 26 February 1975. In June 1987, Thai Airways ordered two DC-10ERs for USD 125 million. This version has 243 seats and can travel 10200 km non-stop. This was probably one of the last orders on the DC-10.
primary users : KLM, Swissair, Continental Airlines, Eastern Airlines, UTA, Air
Afrique, SABENA, Korean Air, Air New Zealand, Canadian Airlines, Northwest
Airlines, Garuda, Thai Airlines (-30ER)
Accommodation:
flight crew : 3 cabin crew : 9
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 255 in two class : 24 first class and 231 coach class seats
( 34 -in pitch) high density seating for 380 passengers
engine : 3 General Electric CF6-50C turbofan engines of 226.83 [KN] (50992.6 [lbf])
dimensions :
wingspan : 50.41 [m], length overall: 55.5 [m], length of fuselage : 51.97 [m]
height : 17.7 [m] wing area : 367.7 [m^2] fuselage exterior width : 6.02 [m]
weights :
operating empty weight : 120742 [kg] max. structural payload : 46180 [kg]
Zero Fuel weight (ZFW) : 166922 [kg] max. landing weight (MLW) : 182798 [kg]
max. take-off weight : 251744 [kg] weight fuel : 108149 [kg] (137770 [litres])
performance :
Never-exceed speed : 0.95 [Mach] (1052 [km/hr]) at 7620 [m]
critical Mach speed : 0.88 [Mach]
max. cruising speed : 955 [km/hr] (Mach 0.88 ) at 9145 [m] (33 [%] power)
economic cruising speed : 908 [km/hr] (Mach 0.83 ) at 9145 [m]
service ceiling : 10180 [m]
range with max fuel and MTOW : 10550 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
Wings : primary two-spar box-type fail-safe wing structure of high-strength aluminium
alloy with Fowler-type double slotted trailing edge flaps with full-span slotted LE
flaps (slats) ,with spoilers airfoil : Douglas. average thickness/chord ratio : 10.3 [%],
sweep angle 3/4 chord: 35.0 [°]
2 engines attached to the wings 1 in the tail, landing gear attached to the wings,
fuel tanks in the wings and in the fuselage
Fuselage : Pressurized all-metal aluminium-alloy stressed-skin structure of circular
section
calculation : *1* (dimensions)
wing chord at root : 10.71 [m]
wing chord at tip : 2.73 [m]
taper ratio : 0.255 [ ]
mean wing chord : 7.29 [m]
wing aspect ratio : 6.91 []
Oswald factor (e): 0.675 []
seize (span*length*height) : 49520 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 1.5 [kg/hr]
fuel consumption (econ. cruise speed) : 8992.6 [kg/hr] (11455.6 [litre/hr]) at 34 [%] power
distance flown for 1 kg fuel : 0.10 [km/kg] at 9145 [m] height, sfc : 38.5 [kg/KN/h]
KLM DC-10-30 PH-DTC c/n 46552 “Frederic Francois Chopin”, with 747-206B PH-BUE c/n 20399 “Rio de la Plata” in the back ground at Schiphol airport
total fuel capacity : 137770 [litre] (108149 [kg])
calculation : *3* (weight)
weight engine(s) dry : 12150.0 [kg] = 17.85 [kg/KN]
weight 38.4 litre oil tank : 3.26 [kg]
oil tank filled with 4.3 litre oil : 3.8 [kg]
oil in engine 8.3 litre oil : 7.5 [kg]
fuel in engine 37.1 litre fuel : 27.22 [kg]
weight fuel lines : 238.1 [kg]
weight engine cowling : 1769.3 [kg]
weight thrust reversers : 1020.7 [kg]
total weight propulsion system : 15220 [kg](6.0 [%])
***************************************************************
Accommodation cabin facilities:
KLM DC-10-30 3-class cabin layout, 9-abreast in Tourist class
Garuda cabin layout with 10-abreast seating
typical 2-class cabin layout for 255 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]
( 2+5+2 ) seating in 29.7 rows
weight passenger seats : 1547.9 [kg]
weight cabin crew seats : 45.0 [kg]
weight flight crew seats : 63.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
high density seating passengers : 380 [pax] at mainly 10 -abreast seating in 43.3 rows,
pitch 80.1 [cm] 31.5 [-in]
pax density, normal seating : 0.84 [m2/pax], high density seating : 0.56 [m2/pax]
weight 7 lavatories : 199.7 [kg]
weight 5 galleys : 537.0 [kg]
weight overhead stowage for hand luggage : 89.2 [kg]
weight 3 wardrobe closets : 25.5 [kg]
weight 3 movie screens : 63.8 [kg]
weight 61 windows (41x28cm) made of acrylic glass : 167.6 [kg]
weight 8 (1.93 x 1.07 [m]) Type A main entry doors : 526.1 [kg]
weight 3 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 280.4 [kg]*
total belly baggage/cargo hold volume : 155.4 [m3]
underfloor belly hold can accommodate : 26 LD3 containers, netto volume : 114.5 [m3]
and : 14.4 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 447 [m3]
passenger compartment volume : 292 [m3]
passenger cabin max width : 5.72 [m] cabin length : 41.45 [m] max cabin height :
2.41 [m]
floor area : 213.6 [m2]
weight cabin facilities : 3559.1 [kg]
safety facilities:
evacuation time with 380 passengers : 49 [sec]
weight 12 hand fire extinguisher : 36 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 165.8 [kg]
Air Afrique DC-10-30 TU-TAL, c/n 46890, the aircraft was hijacked 24 July 1987
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 348.9 [kg]
weight safety equipment & facilities : 581 [kg]
fuselage construction:
fuselage aluminium frame : 22554 [kg]
floor loading (payload/m2): 216 [kg/m2]
weight rear pressure bulkhead : 472.8 [kg]
fuselage covering ( 814.4 [m2] duraluminium 3.09 [mm]) : 6744.1 [kg]
weight floor beams : 5082.7 [kg]
weight cabin furbishing : 3188.2 [kg]
Monarch airlines interior
weight cabin floor : 3020.9 [kg]
weight (sound proof) isolation : 638.1 [kg] TO-noise level : 97.0 [EPNdB]
weight 18953 [litre] main central fuel tanks empty : 1061.4 [kg]
weight 15596 [litre] additional central fuel tank (ACT) empty : 873.4 [kg]
weight empty 450 [litre] potable water tank : 39.8 [kg]
weight empty waste tank : 31.0 [kg]
weight engine mount in tail : 113 [kg]
weight fuselage structure : 43819.6 [kg]
Avionics:
weight VHF radio and Selcal : 9.0 [kg]
weight flight and service attendants intercom : 5.0 [kg]
weight dual cloud-collision radar : 25.0 [kg]
weight monochromatic weather X-band (3.2cm wavelength) radar system : 25.0 [kg]
DC-10 navigation console
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight Avionic Flight Control System : 33.0 [kg]
weight artificial horizons, compass, alti-meters : 7 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight engine monitoring gauges & control switches : 21 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators :
15 [kg]
weight avionics : 151.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to
6400 [m] and gives equivalent of 2440 [m] at 12200 [m]. pressure differential : 0.58
[bar] (kg/cm2) pressurized fuselage volume : 576 [m3] cabin air refreshment time :
3.0 [min]
weight air-conditioning and pressurization system : 328 [kg]
weight APU / engine starter: 113.4 [kg]
weight lighting : 84.2 [kg]
weight triple redundant 207 bar hydraulic system : 167.5 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 63.8 [kg]
weight integrated drive generator (IDG) : 25 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 36.2 [kg]
weight controls : 22.3 [kg]
weight systems : 840.2 [kg]
total weight fuselage : 48951 [kg](19.4 [%])
***************************************************************
total weight aluminium ribs (1620 ribs) : 8251 [kg]
weight engine mounts : 227 [kg]
KLM DC-10-30 PH-DTF flying over the pyramids, painting by Thijs Postma
weight 6 wing fuel tanks empty for total 103221 [litre] fuel : 5780 [kg]
weight wing covering (painted aluminium 3.88 [mm]) : 7695 [kg]
total weight aluminium spars (multi-cellular wing structure) : 11019 [kg]
weight wings : 26965 [kg]
weight wing/square meter : 73.33 [kg]
weight thermal leading-edge anti-icing : 55.5 [kg]
weight high & low speed ailerons (17.44 [m2]) : 640.8 [kg]
weight fin (45.92 [m2]) : 1687.3 [kg]
weight rudder (10.28 [m2]) : 362.5 [kg]
weight tailplane (stabilizer) (96.61 [m2]): 3904.7 [kg]
weight elevators (27.70 [m2]): 549.56 [kg]
weight flight control hydraulic servo actuators: 82.5 [kg]
weight trailing-edge double slotted flaps (62.07 [m2]) : 1939.5 [kg]
weight leading edge slats made of aluminium alloy honeycomb (43.82 [m2]) : 860.5 [kg]
weight spoilers (12.7 [m2]) : 230.9 [kg]
total weight wing construction : 43285 [kg] (35.8 [%])
*******************************************************************
tire pressure main wheels : 12.41 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 389 [km/hr] total tyre footprint : 1.37 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 48 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 59 [ ] Can only operate from unpaved runways with reduced weight
and reduced tyre pressure
wheel pressure : 22153.5 [kg]
weight 10 Dunlop main wheels (1320 [mm] by 528 [mm]) : 1685.8 [kg]
weight 2 nose wheels : 168.6 [kg]
weight hydraulic disc wheel-brakes : 166.9 [kg]
weight Duplex anti-skid units : 10.8 [kg]
weight oleo-pneumatic shock absorbers : 222.6 [kg]
weight wheel hydraulic operated retraction system : 2221.3 [kg]
total weight landing gear : 10995.7 [kg] (4.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 118452 [kg](47.1 [%])
weight oil for 13.3 hours flying : 21.6 [kg]
weight lifejackets : 114.8 [kg]
weight 5 life rafts : 159.4 [kg]
weight catering : 497.2 [kg]
weight water : 397.8 [kg]
weight crew : 972 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 127 [kg]
operational weight empty : 120742 [kg] (48.0 [%])
********************************************************************
weight 255 passengers : 19635 [kg]
weight luggage : 4080 [kg]
weight cargo : 22465 [kg] (cargo + luggage/m3 belly : 164 [kg/m3])
Eastern Airlines N391EA DC-10-30 c/n 47866
zero fuel weight (ZFW): 166922 [kg](66.3 [%])
weight fuel for landing (1.8 hours flying) : 15876 [kg]
max. landing weight (MLW): 182798 [kg](72.6 [%])
max. fuel weight : 228891 [kg] (90.9 [%])
payload with max fuel : 246 passengers + luggage 22853 [kg]
published maximum take-off weight : 251744 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 370 [kg/KN]
power loading (Take-off) 1 PUF: 555 [kg/KN]
max. total take-off power : 680.5 [KN]
calculation : *5* (loads)
manoeuvre load : 1.3 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.0 [g]
design flight time : 3.90 [hours]
design cycles : 12930 sorties, design hours : 50427 [hours]
max. wing loading (MTOW & flaps retracted) : 685 [kg/m2]
wing stress (2 g) during operation : 158 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.82 ["]
max. angle of attack (stalling angle, clean) : 13.76 ["]
max. angle of attack (full flaps) : 17.96 ["]
angle of attack at max. speed : 1.18 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.25 [ ]
lift coefficient at max. angle of attack (clean): 1.28 [ ]
max. lift coefficient full flaps : 1.87 [ ]
drag coefficient at max. speed : 0.0458 [ ]
drag coefficient at econ. cruise speed : 0.0436 [ ]
induced drag coefficient at econ. cruise speed : 0.0089 [ ]
drag coefficient (zero lift) : 0.0346 [ ]
lift/drag ratio at econ. speed : 5.40 [ ]
calculation : *8* (speeds
Emergency stop; An American Airlines plane has buried its nose deep in the mud, while passengers leave the plane through the emergency doors. The pilot decided to abort the take-off from the airport in Grapevine (Texas), due to a defect in the nose wheel. The emergency stop ended at the end of the runway, in the soft ground. Only a few passengers were slightly injured. Photo : AP
Saturday 21 May 1988 American Airlines DC-10-30 N316AA c/n 47846
International scheduled passenger flight AA70 from Dallas (DFW) to Frankfurt, Germany with 14 crew and 240 passengers. First flight : 1973
Airframe hrs : 61322 cycles : 12864 engines : GE CF6-50C2. No people died in the crash and only some slightly injured. Aborted take-off from RW 35L (3471m). RW length measured in google earth comes at 4100m . V1 166 kts, but acceleration to 178 kts at aborting take-off. location : +-100m 32°55’05”N 97°01’47”W
Calculated brake kinetic energy capacity : 2392 [KW]
take-off decision speed (V1) : 302 [km/u] (163 [kt])
Monarch DC-10-30 G-DMCA c/n 48266 taking off from Manchester airport, September 2001 RW24L
lift-off speed (VLOF) : 343 [km/u] (185 [kt]) at pitch angle : 13.2 [°]
take-off safety speed (V2) : 345 [km/u] (186 [kt])
flap retraction speed (V3) at 500m (OW loaded : 242751 [kg]): 351 [km/u] (189 [kt])
steady initial climb speed (V4) : 371 [km/u] (200 [kt])
climb speed (to FL150 with 66 [%] power) : 533 [km/hr] (288 [kt])
max. endurance speed (Vbe): 581 [km/u] min. fuel/hr : 7262 [kg/hr] at height : 7315 [m]
max. range speed (Vbr): 852 [km/u] (0.78 [mach]) min. fuel consumption : 9.85 [kg/km]
at cruise height : 9144 [m]
max. cruising speed : 955 [km/hr] (516 [kt]) at 9145 [m] (power:37 [%])
max. operational speed (Mmo) : 1052 [km/hr] (Mach 0.95 ) at 7620 [m] (power:57 [%])
airflow at cruise speed per engine : 457.9 [kg/s]
speed of thrust jet : 1616 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.72
descent speed 7315 - 3048 [m]: 519 [km/u] (280 [kt])
approach speed 3048 - 500 [m] (clean): 389 [km/u] (210 [kt])
minimum control speed (MCS) Vmca (clean): 334 [km/u] (180 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 182798 [kg]): 290
[km/u] (157 [kt])
Approach speed at MLW 182798 kg (403.000 lbf) : 145 kts (269 km/h)
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing
weight): 269 [km/u] (145 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 207 [km/u]
rate of climb at sea-level ROC (loaded, 66 % power) : 898 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1160 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 685 [m/min]
rate of descent from FL240 to FL100 (7315m > 3048m): 1067 [m/min] (3501 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 457
[m/min] (1499 [ft/min])
calculation : *9* (regarding various performances)
high wheel pressure, can only take off from paved runways
ICAO Aerodrome Reference Code : 4D
FAR TO RW length at standard day, sea level, MTOW 251744 kg (554000 lbs) : 10500 ft > 3200 m, at 259450 kg (571980 lbs) : 11600 ft = 3535 [m] jane’s : FAR TO to 10.7m : 3581 [m]
FAR TO runway length (TOFL) requirement at TOW 251744 [kg] standard day at SL
(= ASDA) : 3172 [m]
Tuesday 28 February 1984 SAS DC-10-30 LN-RKB c/n 46871 “Haakon Viking”
ISP Flight 901 from Oslo (GEN), Norway to New York (JFK), USA with 14 crew and 163 passengers. Touched down late and too fast at RW 04R (2560m long), 1440m past the threshold. The airplane could not stop in time on the wet runway and the crew steered to the right to avoid approach lights and then ended up in shallow water. First flight : 1976 engines : GE CF6-50. No people died in the crash, only a few lightly injured. The airplane suffered substantial damage. location : Thurston Basin +-50m 40°38’47.20”N 73°45’09.23”W
landing run (MLW) : 904 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1757 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2020 [m]
FAR landing runway at MLW 182798 kg (403.000 lbf) : 5960 ft > 1817 [m]
FAR landing runway length requirements at SL : 1809 [m]
max. lift/drag ratio : 10.28 [ ]
climb to 5000 [m] with max payload : 5.15 [min]
climb to 10000 [m] with max payload : 15.85 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 14125 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 242751 [kg] ) : 16000 [m]
calculation *10* (action radius & endurance)
range with max. payload: 8356 [km] with 46180.0 [kg] max. useful load (78.4 [%] fuel)*
range with high density pax: 9534 [km] with 380 passengers (88.5 [%] fuel)*
range with typical two-class pax: 10823 [km] with 255 passengers (99.2 [%] fuel)*
Range with max fuel (111388 kg) : 5500 nm = 10186 km
range with max.fuel : 10920 [km] with 12 crew and 246 passengers and 100.0 [%]
fuel*
ferry range : 11466 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 168950 [litre] fuel : 13729
[km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 3192099 [paskm]
useful load with range 1000km : 46180 [kg]
useful load with range 1000km : 380 passengers
production (theor.max load): 44102 [tonkm/hour]
production (useful load): 44102 [tonkm/hour]
production (passengers): 295645 [paskm/hour]
oil and fuel consumption per tonkm : 0.204 [kg]
calculation *11* (operating cost)
fuel cost per hour (11456 [litre]):6873 [eur] (26 [pax-km/litre fuel])
fuel cost per seat 1000km flight (310 [pax] 2-class seating): 23.25 [eur/1000PK]
oil cost per hour: 6 [eur]
crew cost per hour : 1650 [eur]
list price 2023 : 314 [mln USD]
average flying hours in 1 year : 3280 [hours] technical life : 18 [year]
real average service life : 18 [years]
depreciation - 18 [years] to 10% residual value
economic hours (expected total flying hours): 59040 [hours] is 0 [%] less then cor.
KLM DC-10-30 at the gate at Schiphol with VW T2 bus at the left
design hours 59040 [hours]
financing interest per flying hour : 2153 [EUR]
write off per flying hour : 4417 [EUR]
time between engine failure : 16831 [hr]
can continue fly on 2 engines, low risk for emergency landing for PUF
workhours per day : 10.71 [hr]
average flight hours till crash : 1.92 [mln hr] (587 service years)
safe flight hours till fatality : 18261 [hr] (5.6 service years)
reservation pax liability/flying hour : 7.05 [SDR*] (8.82 [eur])
insurance cost per hour : 751 [eur] insurance rate : 2.1 [%]
The DC-10 could carry a spare engine in a streamlined pod under the wing
engine maintenance cost per hour : 1011.9 [eur]
wing maintenance cost per hour : 207.4 [eur]
fuselage maintenance cost per hour : 107.09 [eur]
tire life (time till worn out) : 95 [cycles]
maintenance cost per hour (excluding engines): 2583 [eur]
direct operating cost per hour: 19453 [eur], DOC per km : 21.42 [eur]
DOC per seat 1000km flight (310 [pax] 2-class seating): 65.80 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 53.61 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.44 [eur/kg] (= DOC/tonkm)
passenger service charge (depart at Schiphol): 11.34 [eur]
security service charge (depart at Schiphol): 10.08 [eur]
airport take-off fee / passenger : 4.85 [eur/pax]
airport landing fee / passenger : 4.85 [eur/pax]
retour ticket price 1000km trip : 213.24 [eur/pax]
price retour ticket Schiphol-Barcelona : 249.43 [eur/pax]
Air New Zealand ZK-NZP was sadly lost at Mt. Erebus, Antarctic, November 1979
accidents with fatalities > see the accident file
Literature :
McDonnell Douglas DC-10 - Wikipedia
Air International April 1994 page 204
Air International April 1990 page 187
Flugzeuge der Welt page 150,151
Jane’s commercial transport aircraft page 189
Aircraft – McDonnell Douglas DC-10 - Northwest Airlines History Center
Jane’s all the world aircraft 1979-80 page
Verkeersvliegtuigen page 69
Amerikaanse vliegtuigbouwers page 68
KLM gegevens page 14
KIJK Mei’83
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/search/results.html?q=airplane+characteristics
confidence rating regarding source data : medium - all information is only available from news, social media or unofficial sources
Post stamp 8F Sabena 50 1923-1973 DC-10-30 registrations in this colour scheme : OO-SLA, OO-SLD, OO-SLE…
DISCLAIMER Above calculations are based on published data, they must be
regarded as indication not as facts.
Calculated performance and weight may not correspond with actual weights
and performances and are assumptions for which no responsibility can be taken.
Calculations are as accurate as possible, they can be fine-tuned when more data
is available, you are welcome to give suggestions and additional information
so we can improve our program. For copyright on drawings/photographs/
content please mail to below mail address
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