Agency: General Electric Company
    Time: 1640 MST
    Altitude: 73.0 miles

UPPER AIR INSTRUMENTS

    Solar radiation: Solar ultra-violet spectrograph (NRL)
    Ionosphere: Ion densities by rf propagation transmitters (NRL).

DATA RECOVERY INSTRUMENTS

    Telemeter: NRL 18 channel PPM/AM system.
    Physical recovery: No blowup installation.

BALLISTIC INSTRUMENTS

    Firing Range
        Theodolites: Two Mitchell and three Askania stations
        Cameras: Two Bowen-Knapp stations
        Radars: Two SCR-584 with T14E1 plotting board
        Doppler: Four stations.

    Airborne
        Beacon: APN-55 S-Band transponder
        Doppler: DOVAP transceiver
        Radio Cutoff: AN/ARW-17. FM control receiver for command fuel cutoff.
        Other: Routine rocket performance instrumentation

ROCKET PERFORMANCE

    Firing angle: 0.0 degrees
    Program angle: 9.3 degrees
    Time to burnout: 58.5/61.2 sec.
    Altitude at burnout: 19.1 miles
    Velocity at burnout: 4220 ft. per sec.
    Time to zenith: 193 sec.
    Altitude to zenith: 73.0 miles
    Time to blowoff:
    Altitude to blowoff:
    Flight duration: 356 sec.
    Impact Coordinates: 40.0 miles north, 1.5 miles west
    Payload weight: 2205 lbs.
    Unfueled rocket weight: 9286 lbs.
    Unfueled rocket C.G.: Approx. 240.2 inches
    Gross weight at takeoff: 28,396 lbs.

BALLISTIC DATA

    Theodolites: Mitchell and Askania produced satisfactory reducible records
    Other: No satisfactory records from other firing range instruments
    Impact location: From theodolite fixes and air and ground search.
 

DATA RECOVERY

    Telemeter: Approx.380 sec. recorded data. Intermittent from poor antenna aspect caused by
        rocket roll
    Physical recovery: Rocket struck intact in salt flats adjacent to White Sands, crater filled
        with water, few fragments found

EXPERIMENTAL DATA

    Solar radiation: No data
    Ionosphere: Signal received 70 to 170 sec from one transmitter - no data.

COMMENTS

    Rocket performance: Trajectory as calculated. No air burst achieved although alcohol tank
        pressurized. Propulsion terminated in two stages by rocket integrator.
    Experiments: Two of three ionosphere antennas probably torn off during flight,
        Spectrograph no recovered.

REPORTS AND PAPERS

    WSPG Report of No. 5 A-4 Rocket Fired 13 June 1946
    Project Hermes Report No. 17, June 1946
    "V-2 Report No. 4" Minutes of V-2 Upper Atmosphere Research Panel on 3 June 1946.
    "Final Report, Project Hermes V-2 Missile Program," by L. D. White, Report No. R52A0510,
        General Electric Co., September 1952.