FIRST STEPS TOWARD SPACE - Smithsonian Institution Libraries

NUMBER 10 243
Test results: t = 70 sec, p' =•• 830 kg, p0 = 80 atm; k = 1.31,
mixture ratio 1:3.9
(nozzle tubes buckled by combustion pressure).
19 March 1941: Firing of 1000 kg thrust rocket engine (nozzle:
profiled Cu-tubes, 4 mm thick, reduced to 2.85 mm for
throat area, 1 path, water coolant velocity 40 m/sec; combustion
chamber: same as on 18 March 1941).
Test results: t = 195 sec, p' = 989 kg, p0 up to 87 atm,
k = 1.46, mixture ratio 1:3 (combustion chamber melted
in places of great material concentration).
20 March 1941: Firing of 100-kg thrust rocket engine (nozzle
and coolant data same as of 19 March 1941, but wall thickness
of throat tubes reduced to 2.50 mm; combustion
chamber data same as of 18 March 1941, but water coolant
velocity ~ 28 m/sec)
Test results: t = 218 sec, p'= 1085 kg, p0 up to 100 atm,
k= 1.4, mixture ratio 1:3.9; during steady state operation:
mixture ratio 1:4.8, c = 2060 m/sec. [see Figures 6 and 7].
16 May 1941: Fired 1000-kg thrust engine, steam cooled:
p0 = 10 atm; t = 10 sec.
4 June 1941: Fired 1000-kg thrust engine, steam cooled:
p0 = 20 atm; t = 20 sec (steel injector started to melt).
17 June 1941: First 1000-kg-thrust engine with steel injector;
steam cooled: p0 = 50 atm; t = 120 sec, injector heat separated;
bolts too weak.
3 November 1941: Mailed to German Air Ministry request
to authorize printing of manuscript "Raketenbomber"
(Rocket-Propelled Bomber).
13 November 1941: Fired 1000-kg-thrust engine with highpressure
combustion chamber: (injector head made of
wound Cu-tubes, combustion chamber of chromium-nickel
alloyed steel and aluminum shell; nozzle consisting of
10-path Cu-tubing). Water coolant flow rate 1.1 liter/sec,
p0 = 80 atm abs, t = 200 sec with increasing thrust and
highly oxygen-rich (about 1:10); water coolant temperature
of 280° C under pressure of 80 atm.
24 November 1941: During discussions showed Mr. Brisken
(German Air Ministry) completed forms for winding tubes
of 100,000-kg-thrust rocket engine [see Figure 8].
11 December 1941: First 1000-kg-thrust engine with highpressure
combustion chamber. Test results: t=140 sec,
p0 = 36 atm abs; water coolant temperature 240° C at
100 atm abs pressure; wound steel tubing of combustion
chamber showed signs of melting at locations of maximum
water coolant temperature for water velocity of 11 m/sec.
12 December 1941: First 1000-kg-thrust engine with highpressure
combustion chamber. Test results: t = 200 sec,
p0 = 40 atm abs; water coolant: 200°C, 60 atm abs,
15m/sec; wound-steel tubing showed signs of melting at
locations of maximum water temperature.
19 December 1941: Reached conclusion that combustion
chambers using evaporating coolants burn through on
combustion-gas side because centrifugal forces displace
portion of liquid coolant to opposite side of tube wall.
February 1942: Development of a coolant evaporator, the
tubing of which is convexly bent towards the combustion
gas side.
March 1942: Construction of 1000-kg-thrust, high-pressure
combustion chamber equipped with new coolant evaporator.
27 April 1942: Termination of firing on large rocket test
stand at Trauen.
FIGURE 7.—Small water-cooled combustion chamber and test instrument in duration test. Water
was heated at 400° C at 100 atm pressure in the cooling system.