C-82 SPECIFICATIONS
| DIMENSIONS | ||
| Overall Length | 77 feet 1 inch | 23.50 meters |
| Overall Width | 106 feet 6 inches | 32.46 meters |
| Overall Height | 26 feet 4.25 inches | 8.03 meters |
| Fuselage Length | 55 feet 2.75 inches | 16.83 meters |
| Fuselage Width | 10 feet 4 inches | 3.15 meters |
| Fuselage Height (from ground on undercarriage) |
13 feet 6 inches | 4.12 meters |
| Cargo Hold Length | 38 feet 5 inches | 11.71 meters |
| Cargo Hold Width | 8 feet 0 inches | 2.44 meters |
| Cargo Hold Height | 8 feet 5 inches | 2.57 meters |
| Cargo Hold Height (under cockpit) |
6 feet 3 inches | 1.92 meters |
| Cargo Hold Deck Area | 308 sq. feet | 28.61 sq. meters |
| Cargo Hold Volume (usable freight volume) |
2598 cu. feet | 73.57 cu. meters |
| Total Internal Volume | 3529 cu. feet | 99.93 cu. meters |
| Main Cabin Door Height | 5 feet 7 inches | 1.70 meters |
| Main Cabin Door Width | 2 feet 11 inches | 0.89 meters |
| Boom Length (from wing trailing edge) |
36 feet 9.5 inches | 11.21 meters |
| Horizontal Stabilizer Width (including tips) |
36 feet 4 inches | 11.07 meters |
| Vertical Stabilizer Heights (including ventral fins) |
16 feet 6 inches | 5.03 meters |
| Propeller Diameters | 15 feet 2 inches | 4.63 meters |
| Wheel Base | 26 feet 6 inches | 8.08 meters |
| Main Wheel Track Width | 28 feet 0 inches | 8.53 meters |
| WING AND TAIL SPECIFICATIONS | ||
| Overall Wing Area | 1400 sq. feet | 130.06 sq. meters |
| Total Aileron Area | 112 sq. feet | 10.41 sq. meters |
| Total Flap Area | 100 sq. feet | 9.29 sq. meters |
| Total Fin Area | 113.2 sq. feet | 10.52 sq. meters |
| Total Rudder Area (including tabs) |
85.6 sq. feet | 7.95 sq. meters |
| Total Tailplane Area | 219 sq. feet | 20.35 sq. meters |
| Total Elevator Area (including tabs) |
91 sq. feet | 8.45 sq. meters |
| Wing Loading (at max weight 54,000 lbs.) |
38.57 lbs. / sq. foot | 188.33 kg / sq. meter |
| Aspect Ratio | 8.1 | |
| Taper Ratio | 2.0 | |
| Main Wing Chord (root) | 17 feet 10 inches / (5.44 meters) | |
| Main Wing Chord (tip) | 8 feet 11 inches (2.72 meters) | |
| Main Wing Section (root) | NACA2418 | |
| Main Wing Section (tip) | NACA4409 | |
| Main Wing Thickness (root) | 18% | |
| Main Wing Thickness (tip) | 9% | |
| Flap Angle | Max Lift Coefficient | Aircraft Weight | Stalling Speed |
| Retracted: 0 deg. | 1.45 | 50,000 lbs. | 98 mph |
| Take-off: 20 deg. | 1.82 | 50,000 lbs. | 88 mph |
| Landing: 40 deg. | 2.02 | 47,200 lbs. | 81 mph |
.jpg)
Early production C-82A s/n: 44-22962, takes to the
air.
Photo: USAF official.
| WEIGHTS | ||
| 39 C-82 Packets built to a
50,000 lbs. max weight. 184 C-82 Packets built to a 54,000 lbs. max weight. |
||
| Serial Numbers | Max Take-off Weight | Max Landing Weight |
| 44-22959 / 44-22968 45-25436 / 45-25438 |
50,000 lbs. (22.68 metric tonnes) |
42,000 lbs. (19.05 metric tonnes) |
| 44-22969 / 44-22993 44-23004 |
50,000 lbs. (22.68 metric tonnes) |
47,200 lbs. (21.41 metric tonnes) |
| 44-22994 / 44-23003 44-23005 / 44-23058 45-57733 / 45-57832 48-568 / 48-587 |
54,000 lbs. (24.49 metric tonnes) |
50,000 lbs. (22.68 metric tonnes) |
| Empty Airframe Weight | 28,000 lbs. | 12700.59 kg (12.70 metric tonnes) |
| Operational Airframe Weight (60% of max take-off weight) |
32,500 lbs. | 14741.75 kg (14.74 metric tonnes) |
| Max Fuel / Payload Weight (40% of max take-off weight) |
21,500 lbs. | 9752.24 kg (9.75 metric tonnes) |
| Max Take-off Weight | 54,000 lbs. | 24493.99 kg (24.49 metric tonnes) |
| Max Zero Fuel Weight (at max weight 50,000 lbs.) |
47,200 lbs. | 21409.56 kg (21.41 metric tonnes) |
| Max take-off weight scenario with max permissible payload | ||
| Operational Airframe Weight | 32,500 lbs. | 14741.75 kg (14.74 metric tonnes) |
| Max Payload Weight | 14,700 lbs. | 6667.81 kg (6.67 metric tonnes) |
| Max Fuel Weight | 6,800 lbs. | 3084.43 kg (3.08 metric tonnes) |
| Max Take-off Weight | 54,000 lbs. | 24493.90 kg (24.49 metric tonnes) |
| ENGINES Pratt & Whitney R-2800 Double Wasp Two 18-cylinder, 2-row, air-cooled radial engines. The -22, -34 and -85 models of the R-2800 were used during military service. The XC-82 Packet prototype was powered by the R-2800-34 engine. The first ten C-82A (s/n: 44-22959 / 44-22968), were powered by the R-2800-22. All subsequent C-82A were powered by the R-2800-85 throughout their careers with the first ten aircraft built later upgraded to this version. During civil service, engines were often modified to later standards, the two listed below: -85AM2H and -CB16 were the ones most often used, especially in the Steward-Davis Jet-Packet program. The -85AM2H has modifications for auto-feathering and Scintilla ignition, the "H" denotes that a crankshaft front and rear damper is incorporated. Other known models of the R-2800 used in post-military service of the C-82A were the R-2800-34H (incorporating a front and rear crankshaft damper), -34W (military water-injection, although these were to be removed or modified to -34M1 standard), -83AM12 (no high-ratio blower gears) and -CB4. |
|||||
| R-2800-22 | R-2800-34 | R-2800-85 | R-2800-85AM2H | R-2800-CB16 | |
| Specification Number | N-1801 | N-1801 | A-8104-A | ? | 8138 |
| Engine Series | C Series | C Series | C Series | ? | CB Series |
| Rating: Take-off | 2100hp @ 2800rpm | 2100hp @ 2800rpm | 2100hp @ 2800rpm | 2100hp | 2500hp @ 2800rpm (@ 4,000 ft. / wet) |
| Rating: Military | 2100hp @ 2800rpm (@ 1,000 ft.) |
2100hp @ 2800rpm (@ 3,000 ft.) |
2100hp @ 2800rpm (@ 3,000 ft.) |
? | 1950hp @ 2800rpm (@ 8,000 ft. / dry) |
| Rating: Normal | 1700hp @ 2600rpm (@ 7,000 ft.) |
1700hp @ 2600rpm (@ sea level) |
1700hp @ 2600rpm (@ 7,300 ft.) |
1800hp | 1800hp @ 2600rpm (@ 8,500 ft.) |
| Displacement | 2804 cu. inches | 2804 cu. inches | 2804 cu. inches | 2804 cu. inches | 2804 cu. inches |
| Weight | 2,359lbs. | 2,359.5 lbs. | 2,375.5 lbs. | 2,365 lbs. | 2,390 lbs. |
| Compression Ratio | 6.75 : 1 | 6.75 : 1 | 6.75 : 1 | 6.75 : 1 | 6.75 : 1 |
| Blower Ratios (Low & High) |
7.29 : 1 9.45 : 1 |
7.29 : 1 9.45 : 1 |
7.29 : 1 9.45 : 1 |
? | 7.29 : 1 8.58 : 1 |
| Prop. Reduction Ratio | .450 : 1 | .450 : 1 | .450 : 1 | ? | .450 : 1 |
| Bore | 5.75 inches | 5.75 inches | 5.75 inches | 5.75 inches | 5.75 inches |
| Stroke | 6.0 inches | 6.0 inches | 6.0 inches | 6.0 inches | 6.0 inches |
| Spline | SAE 60A | SAE 60A | SAE 60A | ? | SAE 60A |
| Magnetos | DF-18LN | DF-18LN | S-18LG-P1 | ? | DLN-10 |
| Carburetion | Bendix/Stromberg PR-58E1-1 |
Bendix/Stromberg PR-58E1-1 |
Bendix/Stromberg PR-58E2-2 |
PT-13F1 | Bendix/Stromberg PR-58E5 |
| Fuel Grade | 100 / 130 Octane | 100 / 130 Octane | 100 / 130 Octane | 100 / 130 Octane | 100 / 130 Octane |
| FUEL CAPACITY For volume to weight conversion - Specific Gravity of 100/130 Octane aviation fuel: 0.71 Total average fuel capacity for C-82A variant is: 2641 US Gal. / 15648.54 lbs. / 7098.060 kg. |
||||
| Serial Numbers | Fuel Tanks | Sub-Total | Total Capacity | Total Weight |
| 44-22959 / 44-22988 | 2 Inboard 2 Outboard |
741 US Gal. each tank 676 US Gal. each tank |
2834 US Gal. | 16792.11 lbs. (7616.78 kg) |
| (C-82N) 45-25436 / 45-25438 |
2 Inboard 2 Outboard |
765 US Gal. each tank 753 US Gal. each tank |
3036 US Gal. | 17989.02 lbs. (8159.68 kg) |
| 44-22989 / 44-23058 45-57733 / 45-57738 |
2 Inboard 2 Outboard |
642 US Gal. each tank 602 US Gal. each tank |
2488 US Gal. | 14741.98 lbs. (6686.85 kg) |
| 45-57739 / 45-57832 48-568 / 48-587 |
2 Inboard 2 Outboard |
669 US Gal. each tank 631 US Gal. each tank |
2600 US Gal. | 15405.61 lbs. (6987.87 kg) |
| OIL CAPACITY | |||
| Serial Numbers | Oil Tanks | Sub-Total | Total Capacity |
| 44-22959 / 44-22988 | 1 in each boom 1 reserve in fuselage |
55 US Gal. each tank 69.5 US Gal. |
179.5 US Gal. (679.48 litres) |
| 44-22989 / 44-23058 45-57733 / 45-57832 48-568 / 48-587 |
1 in each boom | 55 US Gal. each tank | 110 US Gal. (416.40 litres) |
| PERFORMANCE Performance specifications vary widely depending on the conditions figures are based on. Most data presented below is quoted directly from the USAF C-82 Handbook. Some commonly quoted standard C-82 performance figures are as follows: Initial Climb Rate: 950 ft./min. (290 m/min.) Max Range: 3875 statute miles (6236 km) Cruise Speed: 150 mph (241 km/hr.) Max Speed: 248 mph (399 km/hr.) Landing Speed: 95 mph (153 km/hr.) Service Ceiling: 21,200 feet (6462 meters) |
||
| Sea level at 54,000 lbs. max weight | ||
| Take-off Distance | 3,960 feet | 1207 meters |
| Initial Climb Rate (at 136 mph) |
620 feet / min. | 998 m / min. |
| Landing Distance (at 42,000 lbs.) |
1,600 feet | 488 meters |
| Range with various payload weights | ||
| Range (payload 13,000 lbs.) | 1,500 statute miles | 2414 km |
| Range (payload 15,500 lbs.) | 1,000 statute miles | 1609 km |
| Range (payload 18,000 lbs.) | 500 statute miles | 805 km |
| At 45,000 lbs. | ||
| Cruising Speed (at 10,000 ft.) |
218 mph | 351 km/hr. |
| Max Speed (at 17,500 ft.) |
248 mph | 399 km/hr. |
| At 50,000 lbs. | ||
| Gliding Speed | 110 - 120 mph | 177 - 193 km/hr. |
| Stall Speed (flaps up / gear down) |
94 mph | 151 km/hr. |
| Stall Speed (flaps / gear down) |
86 mph | 138 km/hr. |
| Normal Cruise Altitude | 7,000 - 10,000 feet | 2134 - 3048 meters |