Agency: General Electric Company
    Time: 1722 MST
    Altitude: 31.0 miles.

UPPER AIR INSTRUMENTS

    Comments: No upper air research instruments in this rocket

DATA RECOVERY INSTRUMENTS

    Telemeter: PXTA-501, 23 channel NRL pulse sequential system; and 28 channel Hermes
        PWM-FM system.
    Physical recovery: None.

BALLISTIC INSTRUMENTS

    Firing Range
        Theodolites: Two Mitchell and eight Askania stations.
        Cameras: Two Ballistic and three Bowen-Knapp stations
        Telescopes: One station.
        Radar: One modified SCR-584 S-Band station
        Doppler: Four stations.
        Impact location: None

    Airborne
        Beacon: AN/APN-55 (XE-2) S-Band transponder.
        Doppler: DOVAP transceiver
        Radio Cutoff: AN/ARW-17 FM control receiver for command fuel cutoff
        Other: Rocket propulsion and control performance instruments.

ROCKET PERFORMANCE

    Firing angle: 000 degrees true
    Program angle: 7 degrees
    Time to burnout: 59.0 sec.
    Altitude at burnout: 14.6 miles
    Velocity at burnout: 2300 ft. per sec.
    Time to zenith: 118 sec.
    Altitude at zenith: 31 miles
    Time to blowoff:
    Altitude at blowoff:
    Flight duration: 239 sec.
    Impact Coordinates: 10.3 miles North, 12.4 miles West.
    Payload weight: 2200 lbs.
    Unfueled rocket weight: 9,140 lbs.
    Unfueled rocket C.G.: 241 inches
    Gross weight at takeoff: 28,355 lbs.

BALLISTIC DATA

    Theodolites: Mitchell trajectory 0 to 239 sec., Askania trajectory data
    Cameras: Bowen-Knapp data satisfactory; Ballistic cameras for test only,
    Telescope: Trajectory data until after peak
    Radar: Trajectory data 0 to 239 sec.
    Doppler: No data
    Impact location: By optical fix and search.

DATA RECOVERY

    Telemeter: Sporadic during cutoff and when rocket was broadside and rolling, good in latter
        part of flight
    Physical recovery: Nothing recovered, remaining fuels exploded at impact.

COMMENTS

    Rocket performance: Takeoff irregular, roll began shortly after. Propulsion normal to 40 sec.,
        then far below normal. Roll rate increased to 80 RPM.

REPORTS AND PAPERS

    Report on a-4 Rocket No. 19, Project Hermes Report No. 55204, General Electric Company.
    Preliminary Report of Firing of V-2 No. 19, White Sands Proving Ground.
    Report No. 695, by H. P. Hitchcock, Ballistic Research Laboratories, Aberdeen Proving Ground,
        April 1949.
    "V-2 Report No. 8," Minutes of Meeting of the V-2 Upper Atmosphere Research Panel on
        28 January 1947.
    "Final Report, Project Hermes V-2 Missile Program," by L. D. White, Report No. R52A0510,
        General Electric Company, September 1952.