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| Goddard series L sec - Rocket equipped with a cluster of four combustion chambers, each 5.75 in. in diameter. 38,163 bytes. 287 x 367 pixels. |
Tests of the Goddard L Section A covered development of a nitrogen-pressured flight rocket using 10 in, motors based on the K series and ran from May 11 to November 7, 1936 (L1-L7). Length of the L Series Section A rockets varied from 10 ft 11 in, to 13 ft 6 1/2 in.; diameter 18 in.; empty weight 120 to 202 lb; loaded weight 295 to 360 lb; weight oxygen about 78 lb; weight gasoline 84 lb; weight nitrogen, 4 lb.
Liftoff Thrust: 280 kgf. Total Mass: 163 kg. Core Diameter: 0.5 m. Total Length: 4.1 m.
These would run through August 9, 1938 and included 30 flight tests of 10-in.-diameter motors, in nitrogen-pressured rockets. The series was divided into three sections: A, B, and C. Section A covered development of a nitrogen-pressured flight rocket using 10 in, motors based on the K series and ran from May 11 to November 7, 1936 (L1-L7). Length of the L Series Section A rockets varied from 10 ft 11 in, to 13 ft 6 1/2 in.; diameter 18 in.; empty weight 120 to 202 lb; loaded weight 295 to 360 lb; weight oxygen about 78 lb; weight gasoline 84 lb; weight nitrogen, 4 lb.
Rocket achieved altitude 200 ft above 80-ft tower; duration 5 sec; landed 300 ft from tower.
Rocket achieved 200 ft vertically in 5 sec, then combustion chamber burned through; weight oxygen 40 lb; weight gasoline 46 lb; weight nitrogen 4 lb; fell 20 ft from tower.
Rocket equipped with a cluster of four combustion chambers, each 5.75 in. in diameter; length 13 ft 6.5 in.; altitude about 200 ft; fell near tower. The L series included four proving-stand tests and three flight test attempts, of which all were successful. Average interval between tests 25 days