CAPTURED GERMAN V-2 ROCKET (NUMBER 33) SEPT 2,1948
UPPER AIR ROCKET SUMMARY V-2
NO. 33
IDENTIFICATION 2 September 1948
Time of firing: 1800 MST
Agency: University of Michigan for SCEL
Altitude: 93.6 miles
UPPER AIR INSTRUMENTS
Density-pressure-temperature: SCEL sound grenades. Shock wave angle measure-
ment for temperature. Ram and cone surface pressure gages for temperature.
Composition: Two evacuated air-sampling bottles with associated timer and pyro-
technic opening and sealing devices
DATA RECOVERY INSTRUMENTS
Telemeter: PXTA-501, 23-channel PPM-AM system
Physical recovery: Warhead control compartment separation by TNT
BALLISTIC INSTRUMENTS
Firing Range
Theodolites: Two Mitchell and seven Askania stations
Cameras: Two ballistic and three Bowen-Knapp stations
Telescopes: Four stations
Radar: One modified SCR-584 S-band station
Airborne
Beacon: AN/APN-55 S-band transponder
Radio Cutoff: AN/DRW-37 FM control receiver for command blowoff and cutoff
Aspect: Three Giannini heliograph cameras
Other: Routine rocket propulsion and control performance instrumentation
(G. E.)
ROCKET INFORMATION
Payload weight: 2535 lb
Unfueled rocket weight: 8422 lb
Takeoff weight: 27,840 lb
Flight duration: 600 sec estimated
ROCKET PERFORMANCE
Program angle: Seven degrees North
Time to burnout: 65.3 sec
Velocity at burnout: 4800 ft/sec
Altitude at burnout: 123,200 ft
Time to zenith: 225 sec
Altitude at zenith: 93.6 miles
Time to tail blowoff: 370 sec
Altitude at tail blowoff: 276,000 ft
Impact coordinates: Main body - 39.5 mi. north, 2.9 mi. west of launcher; warhead
40 mi. north, 3.5 mi. west of launcher
BALLISTIC DATA
Theodolites: Askania trajectory data form 1.6 to 69.6 sec
Radar: Trajectory data from 0 to 369.5 sec
DATA RECOVERY
Telemeter: Data from 0 to 18 sec, and from 50.5 to 52.5 sec; none thereafter
Physical recovery: Two air-sampling bottles recovered. Three heliographs in
excellent condition.
EXPERIMENTAL DATA
Upper air composition: No data
No air samples - one bottle seal ruptured at impact, opener failed on other bottle
Because of the telemeter failure no information was obtained from the shock wave
angle experiment or the cone pressure experiment
COMMENTS
Rocket modifications: Four Pirani gages mounted on extension rods were placed at
90-degree intervals, eight in. from the longitudinal axis of a 40-degree right
circular cone. The rods were driven through an excursion of 8 in. with a period
of about 3 sec in a direction parallel to the cone axis so as to intercept the
shock wave.
An opening for the ram-pressure Pirini gage was placed in the tip of the
cone and four openings for cone side-pressure gages were placed at 90-degree
intervals on the cone surface
The holes for the grenades were located radially in the base of the warhead
Rocket performance: Excellent
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