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weight and performance calculations for the Lockheed 9D Orion
Lockheed 9D Orion
role : medium weight passenger aircraft
importance : ****
first flight : operational : May 1931
country : United States of America
design : Richard A. von Hake
production : 35 aircraft
general information :
First airliner with retractable landing gear, it was faster then contemporary military
aircraft. Last wooden monoplane design built by Lockheed. It competed in the 1931
Bendix air race. New CAA rules in 1934 (co-pilot & multi-engine mandatory) ended the
use of the Orion as passenger aircraft.
users : Bowen air lines, Northwest Airlines, American Airways
crew : 1 passengers : 6
engine : 1 Pratt & Whitney R-1340-S1D1 Wasp air-cooled 9 -cylinder radial engine 500
[hp] (372.9 KW) supercharged engine, constant power to height : 2286 [m]
dimensions :
wingspan : 13.04 [m], length : 8.64 [m], height : 2.95[m]
wing area : 27.32 [m^2]
weights :
max.take-off weight : 2450 [kg]
empty weight operational : 1606 [kg] useful load : 525 [kg]
performance :
maximum speed :322 [km/hr] at sea-level
cruise speed :306 [km/u] op 100 [m]
service ceiling : 6700 [m]
range : 900 [km]
description :
low-winged monoplane with retractable landing gear with tail wheel
tapered wing with split flap
engine in the nose, fuel tanks in the wing, landing gear attached to the wing
construction : fuselage > semi-monocoque wooden fuselage covered with plywood,
wooden wing covered with plywood
airscrew :
ground adjustable 2 -bladed metal Hamilton Standard tractor propeller with max.
efficiency :0.72 [ ]
estimated diameter airscrew 2.80 [m]
power loading prop : 133.16 [KW/m]
prop efficiency ratio: 9.48 [1/s]
angle of attack prop : 20.29 [ ]
tip/speed little higher then speed of sound, need for thin metal tips
reduction : 1.00 [ ]
airscrew revs : 2200 [r.p.m.]
pitch at Max speed 2.44 [m]
blade-tip speed at Vmax and max revs. : 335 [m/s]
calculation : *1* (dimensions)
measured wing chord : 2.09 [m] at 50% wingspan
mean wing chord : 2.10 [m]
wing aspect ratio : 6.22 []
seize (span*length*height) : 332 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 5.2 [kg/hr]
fuel consumption(cruise speed) : 85.8 [kg/hr] (117.0 [litre/hr]) at 77 [%] power
distance flown for 1 kg fuel : 3.57 [km/kg] at 3350 [m] height, sfc : 297.1 [kg/kwh]
estimated total fuel capacity : 391 [litre] (286 [kg])
calculation : *3* (weight)
weight engine(s) dry : 346.0 [kg] = 0.93 [kg/KW]
weight 29.8 litre oil tank : 2.54 [kg]
oil tank filled with 2.8 litre oil : 2.5 [kg]
oil in engine 2.1 litre oil : 1.9 [kg]
fuel in engine 2.5 litre fuel : 1.86 [kg]
weight 49.8 litre gravity patrol tank(s) : 7.5 [kg]
weight gas starter : 9.1 [kg]
weight NACA cowling 16.7 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 33.5 [kg]
total weight propulsion system : 419 [kg](17.1 [%])
***************************************************************
fuselage skeleton semi-monocoque (wood gauge : 6.56 [cm]): 265 [kg]
cabin layout : pitch : 87 [cm] (1+1) seating in 3.0 rows
weight 1 fire extinguisher : 3 [kg]
weight 6.0 windows : 5.40 [kg]
passenger cabin width : 1.14 [m] cabin length : 2.61 [m] cabin height : 1.80 [m]
weight cabin furbishing : 10.60 [kg]
weight cabin floor : 19.02 [kg]
bracing : 17.3 [kg]
fuselage covering ( 14.1 [m2] plywood 10.3 [mm]) : 86.6 [kg]
weight radio navigation equipment : 6.0 [kg]
weight instruments. : 5.0 [kg]
weight lighting : 1.5 [kg]
weight electricity generator : 2.7 [kg]
weight controls : 5.0 [kg]
weight seats : 35.0 [kg]
weight air conditioning : 9 [kg]
weight engine mounts & firewalls : 19 [kg]
total weight fuselage : 487 [kg](19.9 [%])
***************************************************************
weight 2.6 [mm] plywood wing covering : 46 [kg]
total weight wooden ribs (64 ribs) : 146 [kg]
weight fuel tanks empty for total 341 [litre] fuel : 27 [kg]
load on front upper spar (clmax) per running metre : 1956.7 [N]
load on rear upper spar (vmax) per running metre : 544.9 [N]
total weight 4 wooden spars : 200 [kg]
weight wings : 391 [kg]
weight wing/square meter : 14.31 [kg]
cantilever wing without bracing cables
weight rubber de-icing boots : 14.3 [kg]
weight fin & rudder (2.0 [m2]) : 28.5 [kg]
weight stabilizer & elevator (3.1 [m2]): 44.2 [kg]
weight split flap(1.4 [m2]) : 12.8 [kg]
total weight wing surfaces & bracing : 518 [kg] (21.2 [%])
*******************************************************************
wheel pressure : 1225.0 [kg]
weight 2 wheels (880 [mm] by 135 [mm]) : 54.5 [kg]
weight tailwheel(s) : 5.9 [kg]
weight wheel hydraulic operated retraction system : 11.6 [kg]
weight undercarriage with axle 101.9 [kg]
total weight landing gear : 173.9 [kg] (7.1 [%]
*******************************************************************
********************************************************************
calculated empty weight : 1598 [kg](65.2 [%])
weight oil for 3.5 hours flying : 18.4 [kg]
calculated operational weight empty : 1616 [kg] (66.0 [%])
published operational weight empty : 1606 [kg] (65.6 [%])
___o___
"
weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 172 [kg]
********************************************************************
operational weight empty: 1869 [kg](76.3 [%])
weight 6 passengers : 462 [kg]
weight luggage & freight : 63 [kg]
operational weight loaded: 2394 [kg](97.7 [%])
fuel reserve : 56.0 [kg] enough for 0.65 [hours] flying
operational weight fully loaded : 2450 [kg] with fuel tank filled for 79 [%]
published maximum take-off weight : 2450 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 6.57 [kg/kW]
power loading (operational without useful load) : 5.01 [kg/kW]
total power : 372.9 [kW] at 2200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 6.2 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.7 [g]
design flight time : 2.35 [hours]
design cycles : 10309 sorties, design hours : 24265 [hours]
operational wing loading : 671 [N/m^2]
wing stress (3 g) during operation : 141 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.88 ["]
max. angle of attack (stalling angle) : 14.32 ["]
angle of attack at max. speed : -0.15 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. angle of attack : 1.30 [ ]
max.lift coefficient full flaps : 1.37 [ ]
lift coefficient at max. speed : 0.14 [ ]
induced drag coefficient at max. speed : 0.0013 [ ]
drag coefficient at max. speed : 0.0226 [ ]
drag coefficient (zero lift) : 0.0213 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 2364 [kg]): 118 [km/u]
stalling speed at sea-level with full flaps : 115 [km/u]
landing speed at sea-level : 135 [km/hr]
min. drag speed (max endurance) : 212 [km/hr] at 3350 [m](power :39 [%])
min. power speed (max range) : 212 [km/hr] at 3350 [m] (power:39 [%])
max. rate of climb speed : 194.4 [km/hr] at sea-level
cruising speed : 306 [km/hr] at 3350 [m] (power:73 [%])
design speed prop : 314 [km/hr]
maximum speed : 322 [km/hr] at 100 [m] (power:103 [%])
climbing speed at sea-level (loaded) : 336 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 143.8 [km/u]
emergency/TO power : 550 [hp] at 2476 [rpm]
static prop wash : 182 [km/u]
start time : 9 [s]
take-off distance at sea-level : 205 [m]
lift/drag ratio : 13.13 [ ]
climb to 1000m with max payload : 3.07 [min]
climb to 2000m with max payload : 6.11 [min]
climb to 3000m with max payload : 9.30 [min]
practical ceiling (operational weight 1869 [kg] ) : 8143 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:2407 [kg] ) : 6828 [m]
calculation *10* (action radius & endurance)
published range : 900 [km] with 1 crew and 500.1 [kg] useful load and 88.1 [%] fuel
range : 811 [km] with 1 crew and 525.0 [kg] useful load and 79.4 [%] fuel
range : 822 [km] with 6.0 passengers with each 10 [kg] luggage and 80.5 [%] fuel
Available Seat Kilometres (ASK) : 4932 [paskm]
max range theoretically with additional fuel tanks total 1026.7 [litre] fuel : 2683 [km]
useful load with range 500km : 612 [kg]
useful load with range 500km : 6 passengers
production (useful load): 187.31 [tonkm/hour]
production (passengers): 1835.40 [paskm/hour]
oil and fuel consumption per tonkm : 0.49 [kg]
oil and fuel consumption per paskm : 0.05 [kg]
fuel cost per paskm : 0.05 [eur]
crew cost per paskm : 0.08 [eur]
economic hours : 12775 [hours] is less then design hours
time between engine failure : 150 [hr]
in case of engine failure only option is emergency landing
writing off per paskm : 0.05 [eur]
insurance per paskm : 0.08 [eur]
maintenance cost per paskm : 0.25 [eur]
direct operating cost per paskm : 0.50 [eur]
direct operating cost per tonkm : 5.03 [eur]
Literature :
Praktisch handboek vliegtuigen deel 2 page
Piston engined airliners page
Lockheed Model 9 Orion - Wikipedia
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
(c) B van der Zalm 18 September 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4
