Time of firing: 1619 MST
    Agency: Air Research and Development Command
    Altitude: 2.6 miles

UPPER AIR INSTRUMENTS

        Skin temperature experiment: Nickel temperature-sensitive elements, com-
            mutated in one arm of ac resistance bridge, to sense heat change in flush-
            mounted thin steel diaphragms distributed along rocket skin (B. U.)
        Emission spectrum experiment: High-powered pulsed transmitter operating in the
            neighborhood of 1.4 Mc to create electrostatic field resulting in emission glow
            (Tufts College and AFCRC)
        Phototube experiment: Six multiplier phototubes, mounted in groups of three on
            opposite sides of warhead, to measure light radiation of electrostatic probe
            experiment (AFCRC)
       Vertical incidence ionosphere experiment: Synchronized ground and rocketborne
            equipment to measure delay time of low-frequency pulse traveling through the
            E layer by comparison with travel time of undelayed high-frequency signal
            (AFCRC)
        Luxembourg experiment and artificial airglow: Intermittently pulsed "disturbing"
            transmitter; pulsed transmitter to radiate "wanted" signal; phototube detectors
            with filters and cameras. (Tufts College, University of Utah, AFCRC.)
        Acoustical studies: Meteoric impacts and acoustic noise. One condenser and one
            crystal microphone. (Temple University).
        Cosmic radiation particle detection experiment: Two sealed cadmium covered
            paraffin spheres containing nuclear emulsion plates, and two sealed rectangular
            iron boxes containing nuclear emulsion plates and lead, placed in Zone C of
            warhead. (U. of Chicago)
        Soft solar x-ray studies: Packets each containing photographic film with a stepped-
            wedge type aluminum filter, were placed on surface of rocket (AFCRC)

ROCKET PERFORMANCE INSTRUMENTS

    Beacon triangulation studies: Triangulation system used to obtain an accurate trajec-
        tory. Airborne 470-493.5 Mc beacon transmits range pulses to 4 ground
        stations. (AFCRC).
    Data transmission utilizing television and beacon techniques: Airborne television
        camera and transmitter to supply observations of ground and parachute per-
        formance. Portion of television raster utilized for ranging. (AFCRC, B. U.,
        and Tufts College). Project Albert III: (Aero-Medical Lab., WPAFB).

DATA RECOVERY INSTRUMENTS

    Telemeter: NRL AN-DKT-2 (XN-1) PPM-AM telemetering system operating at
        frequency of 1025 Mc  30 channels. G. E. telemetering system - 30 channels.
        BRL telemetering equipment (Hermes)
    Physical recovery: Blossom warhead to be separated from rocket body by means of
        four pistons actuated by explosive charge. To be lowered by parachute after
        separation. One red 64-ft nylon ribbon main canopy used in conjunction with a
        16-ft nylon ribbon drag parachute.

BALLISTIC INSTRUMENTS

    Firing Range
        Theodolites: Three Mitchell and eight Askania stations
        Cameras: Three ballistic and three Bowen-Knapp stations
        Telescopes: Three stations
        Radar: Two S-band radars
        Doppler: Six stations
        Impact location: E and C stations of the impact point computer were operated

    Airborne
        Beacon: APN/55 - S-band
        Radio Cutoff: One ARW-37 radio receiver operating at 54.5 Mc was located in
        control compartment for use in fuel cutoff and parachute ejection
        Other: Routine rocket performance instrumentation

ROCKET INFORMATION

    Unfueled rocket weight: 9996 lb
    Unfueled rocket C.G.: 260.5 in.
    Gross weight at takeoff: 29,195 lb

ROCKET PERFORMANCE

    Program angle: Two degrees at 13 sec
    Time to burnout: 24.7 sec (fuel cutoff)
    Velocity at burnout: 620 ft/sec
    Altitude at burnout: 1.7 miles
    Time to zenith: 42.5 sec
    Altitude at zenith: 2.6 miles
    Time to tail blowoff: 48.2 sec (signal given but not effected)
    Flight duration: 82.9 sec
    Impact coordinates: Main body and warhead - approximately 3/4 mi. west and 1/2
        mi. north of the launcher. Nose tip - 200 yd south of main impact

BALLISTIC DATA

    Theodolites: Askania - to impact, Mitchell - to impact
    Cameras: Missile did not climb high enough during burning period for recording of
        images by ballistic cameras. Bowen-Knapp - for approximately 17 sec of flight.
    Telescopes: Tracked main body to impact
    Radar: Good signal until 10.5 sec, when beacon went out abruptly
    Doppler: Noisy signal on six stations, faded out at about 26.7 sec
    Impact location: Trackers at E and C stations followed the rocket to impact.

DATA RECOVERY

    Telemeter: NRL telemetering equipment functioned normally throughout flight of
        missile. Hermes telemetry - good signal obtained.
    Physical recovery:
        Blossom IV-C experiment - after two explosions in rocket, attempt was made to
            save warhead and parachute by giving warhead blowoff command at 48.2
            seconds. However, command was not effected.
        Parachute experiment - parachute ejection did not take place
        Instrument rack with all instrument was badly damaged by impact and fire.
            Two cameras in main body were recovered in good but not operable con-
            dition. Nose cone was badly broken up. Parachute was badly burned.

EXPERIMENTAL DATA

    Because of the nature of the flight, no data were obtained from the soft x-ray
        studies, phototube experiment, vertical incidence ionosphere experiment,
        acoustical studies, particle detection experiment, emission spectrum experi-
        ment, Luxembourg experiment and artificial airglow
    Skin temperature measurements: Measurements obtained for duration of short
        flight
    Beacon triangulation studies: Good signal to impact
    Data transmission utilizing television and beacon techniques: Good signals until
        second explosion

COMMENTS

    Rocket modifications: This was the third V-2 to carry an elongated nose section,
        giving an additional length of one diameter to the rocket
    Rocket performance: After firing time had been delayed twice, takeoff appeared
        normal. At 10.7 sec small explosion occurred in tail section and west fin
        disintegrated; missile began to roll and yaw. Second explosion at 24.2 sec in
        tail section and missile began to tumble. Blowoff command given at 48.2 sec,
        but command was not effected.
    Other: Upon impact a high order explosion occurred, scattering parts and fragments
        over a wide area; flames of the burning fuel appeared to be about 80 ft high.
        The instrument and parachute compartment remained at the point of impact.

REPORTS AND PAPERS

    "Rocket-Borne Television Camera Utilizing the RCA Type 5527 Iconoscope," W. C.
        Moore, Part II, Technical Note No. 7, Upper Atmosphere Research Laboratory,
        Boston University, 4 April 1950, Contract A F19(122)-36
    "Research in the Physical Properties of the Upper Atmosphere, With Special
        Emphasis on Acoustical Studies with V-2 Rockets," Research Institute of
        Temple University, Report No. 6, 8 February 1950, Contract W19-122-ac-12
    "Investigation of the Ionosphere Utilizing Sounding Rockets," Upper Atmosphere
        Research Laboratory, Boston University, Report No. 2, 1 September - 30
        November 1949, Contract A f19(122)-36