Time of firing: 2016 MST
    Agency: Air Research and Development Command
    Altitude: 1.9 miles

UPPER AIR INSTRUMENTS

    Solar soft x-ray studies: A number of packets, each containing photographic film
        with a single thickness filter, were placed on surfaces of the rocket (AFCRC)
    Skin temperature experiment: Nickel temperature-sensitive elements, commutated
        in one arm of ac resistance bridge, to sense heat change in flush-mounted thin
        steel diaphragms distributed along rocket skin (B. U.)
    Atmospheric composition studies: Grating spectrograph, Littau type, aperture f2.9,
        electrodeless discharge light source (AFCRC)
    Emission spectrum experiment: Crystal controlled rf generator operating at 1.4 Mc
        and square wave modulated at 979 cps to create a strong electrostatic field.
        Rocket was split by insulating section just forward  of control compartment and
        operated as a doublet antenna for this generator (Tufts College and AFCRC)
    Luxembourg experiment: Pulsed transmitter operating at 3.5 Mc and synchronized
        with emission spectrum generator to investigate cross modulation (U. of Utah,
        Tufts College, and AFCRL)
    Synchronized beacon: A 493.5-470 Mc beacon provides synchronizing signals from
        ground transmitter for emission spectrum and Luxembourg experiments (HAFB,
        Oklahoma A and M, and AFCRC)
    Photoelectric detection of artificial airglow: Six multiplier phototubes with associ-
        ated interference filters and circuits installed in instrument compartment (Naval
        Ordnance Test Station)
    Photographic detection of artificial airglow: Eight motion picture GSAP16-mm
        cameras (modified and re-geared) for recording intensity of emission spectrum
        experiment glow discharge. Four located in instrument compartment and four in
        missile body. (AFCRC)
    Night Sky infrared measurements: Phototube with appropriate filter and amplifier
        to measure infrared radiation in the night sky (AFCRC and HAFB)
    Common power supply: Three 2.8-kva inverters, each powered by eight type ER-8-
        30 batteries. Output of two inverters used for Luxembourg equipment, and out-
        put from third served as common power supply for rocket.

DATA RECOVERY INSTRUMENTS

    Telemeter: NRL telemetering system. Hermes telemetering system.

BALLISTIC INSTRUMENTS

    Firing Range
        Theodolites: Two Mitchell stations
        Cameras: Two Bowen-Knapp stations
        Radar: S-band radar, MPQ/12

ROCKET INFORMATION

    Unfueled rocket weight: 10,407 lb
    Unfueled rocket C.G.: 267.9 in.
    Gross weight at takeoff: 30,067 lb

ROCKET PERFORMANCE

    Program angle: 7 degrees
    Time to zenith: 33.5 sec
    Altitude to zenith: 1.9 miles
    Flight duration: Approximately 65.1 sec
    Impact coordinates: 3818 ft at azimuth of 110 degrees 37 ft

BALLISTIC DATA

    Radar: Beacon went out at 16.0 sec. Radar was returned to straight reflection and
        tracked rocket from 18.0 sec to impact in automatic.

EXPERIMENTAL DATA

    No experimental results due to nature of flight

COMMENTS

    Rocket modifications: The typical V-2 rocket was modified by increasing the length
        of the missile by one diameter. Nose section differed from previously launched
        Blossoms in that recovery by parachute was not a test objective. An insulated
        section required for the Luxembourg and emission spectrum experiments was
        used in place of the original parachute compartment
    Rocket performance: Preliminary stage and takeoff appeared normal and missile
        rose as expected for approximately 15 sec. At approximately 15.5 sec an explo-
        sion occurred in the propulsion section of missile; a second explosion occurred
        at approximately 18.5 sec, and a third, at 19.5 sec, which destroyed a large
        portion of the tail section.