Goddard Series P Sec - Rockets of large fuel capacity, with the rocket motor, pumps, and turbines previously developed. 44,529 bytes. 436 x 325 pixels.

Section C tests would run through October 10, 1941 and represent the final Goddard rocket flight tests. The series of twenty-four static and flight tests (P13-P36) was made with rockets of large fuel capacity, with the rocket motor, pumps, and turbines previously developed. These rockets averaged nearly 22 ft in length, and were 18 in, in diameter. They weighed empty from 190 to 240 lb. The liquid-oxygen load averaged about 140 lb, the gasoline 112 lb, making "quarter-ton" loaded rockets.

Liftoff Thrust: 310 kgf. Total Mass: 220 kg. Core Diameter: 0.5 m. Total Length: 6.7 m.

• Goddard Series P Section C rocket tests

  Section C tests would run through October 10, 1941. The series of twenty-four static and flight tests (P13-P36) was made with rockets of large fuel capacity, with the rocket motor, pumps, and turbines previously developed. These rockets averaged nearly 22 ft in length, and were 18 in, in diameter. They weighed empty from 190 to 240 lb. The liquid-oxygen load averaged about 140 lb, the gasoline 112 lb, making 'quarter-ton' loaded rockets.

• Goddard Series P Section C rocket static test

  Static test at flight tower; steady 40-sec run; lift 760 lb.

• Goddard Series P Section C rocket static test

  Static test, flame hot, apparently large lift; ground behind dame deflector looked melted.

• Goddard Series P Section C rocket static test

  Static test, steadier run 43.5 sec, longest to date; red-hot stones seen to fly up out of cement gas deflector.

• Goddard Series P Section C rocket flight test

  First flight with pumps, altitude 300 ft; velocity low, 10-15 mph.

• Goddard Series P Section C rocket static test

  Static test, highest lift so far recorded, 985 lb.

• Goddard Series P Section C rocket flight test

  Second flight with pumps, altitude 250 ft; then heeled away from tower.

• Goddard Series P Section C rocket static test

  Static test: duration 34 sec; average thrust 825+ lb; gas ejection velocity 4060 ft/sec; average thrust per pound of fuel per second 128; mechanical horsepower 3040; liquid oxygen 131.7 lb; gasoline 91.5 lb; ratio oxygen to gasoline 1.43.

• End of Goddard sounding rocket tests

  The Goddard P series pump-turbine tests had run from November 1939-October 1941. The series included 15 proving-stand tests and nine attempts at flight tests, of which only two resulted in flights. Average interval between tests was 28 days. This also ended Goddard development of liquid fuel rockets for space flight. Beginning in September 1941 with the impending involvement of the US in the world war, the Goddard rocket establishment worked under contracts with the Bureau of Aeronautics of the Navy Department and the Army Air Forces. Up to that point Goddard's team had completed 103 liquid rocket proving stand tests and made 48 attempts at flight tests, of which 31 resulted in rocket flights

• 482 - Goddard, Robert H, Collected Papers of Robert H Goddard, .