The TR-1 was a development of the U-2R, which was a major redesign of the original

U-2. The R, and related, are a third larger than the original U-2, aside from appearance

and engine - with the exception of the S, they have little in common and the airframe is

still primarily metal.

**U-2A/C/D**Construction: Conventional aluminum monococque

Length: 49.7 feet

Wingspan: 80 feet, 2 inches

Wing Area: 600 square feet

Height: 15 feet, 2 inches (at tail)

Empty Weight: 14,250 pounds

Maximum Gross Take-Off Weight: 24,150 pounds

Maximum Speed: over 430 mph

Operational Ceiling: over 70,000 feet

Maximum Unrefueled Range: 3,000 nautical miles

Armament: none

Powerplant Data: Pratt & Whitney(P & W) J57-P-37/ J57-P-37A with 10,500 pounds of thrust

updated to: P & W J57-P-31/ J57-P-31A with 11,200 pounds of thrust

updated to: P & W J75-P-13/ J75-P-13A with 15,800 pounds of thrust

updated to: P & W J75-P-13B axial flow turbojet with 18,500 pounds of thrust

**U-2R, and TR-1, U-2S, TU-2S(2 seat trainer)**Construction: Conventional aluminum monococoque, with some composites

Length: 63.1 feet

Wingspan: 104.8 feet

Wing Area (gross): 1,000 square feet

Height: 16.7 feet (at tail)

Empty Weight: Classified

Maximum Takeoff Weight:40,000 lb.

Maximum Speed: over 430 mph

Operational Ceiling: over 70,000 feet

Maximum Unrefeuled Range: over 3,000 nautical miles

Aramament: none

Powerplant Data:

U-2R: Pratt & Whitney J75-P-13B with 18,500 pounds thrust

U-2S: General Electric F118-GE-101 with 18,300 pounds thrust

https://www.blackbirds.net/u2/u2specs.html