Study of the application of hydrogen fuel to long-range subsonic transport aircraft. Volume 2. Final report, Feb--Oct 1974

Technical Report · Wed Jan 01 04:00:00 EST 1975

OSTI ID:7343444

Brewer, G D; Morris, R E; Lange, R H; Moore, J W

The feasibility, practicability, and potential advantages and disadvantages of using liquid hydrogen as fuel in long range, subsonic transport aircraft of advanced design were studied. Both passenger and cargo-type aircraft were investigated. To provide a valid basis for comparison, conventional hydrocarbon (Jet A) fueled aircraft were designed to perform identical missions using the same advanced technology and meeting the same operational constraints. The liquid hydrogen and Jet A fueled aircraft were compared on the basis of weight, size, energy utilization, cost, noise, emissions, safety, and operational characteristics. A program of technology development was formulated.

• Research Organization: Lockheed-California Co., Burbank (USA)
• OSTI ID: 7343444
• Report Number(s): N-75-30163; NASA-CR-132559; LR-26752-2
• Country of Publication: United States
• Language: English

Related Subjects

08 HYDROGEN
080600 -- Hydrogen-- Industrial & Commercial Use-- (-1989)
33 ADVANCED PROPULSION SYSTEMS
330800* -- Emission Control-- Alternative Fuels
AIRCRAFT
COMPARATIVE EVALUATIONS
COST
DESIGN
EMISSION
ENERGY CONSUMPTION
FEASIBILITY STUDIES
FUEL CONSUMPTION
FUELS
HYDROGEN FUELS
JET ENGINE FUELS
NOISE
PERFORMANCE
SAFETY
SIZE
SYNTHETIC FUELS
USES
WEIGHT