Time of firing: 1214 MST
    Agency: Air Research and Development Command
    Altitude: 81 miles

UPPER AIR INSTRUMENTS

    Density-pressure-temperature:
        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 emis-
            sion glow (AFCRC)
        Oblique incidence ionosphere propagation experiment: Gound-trnsmitted
            signal travels over very long path. Receivers both in rocket and on ground.
            Rocket transmitter retransmits signal received in rocket to ground
            receiver. Measures attenuation of wave passing downward through E layer
            reflected from F layer. (B. U.)
        Vertical incidence ionosphere propagation experiment: Synchronized ground and
            airborne 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 detec-
            tors with filters and cameras. There is some evidence that glow is localized
            in immediate vicinity of rocket. (Tufts College, Utah U. and AFCRC.)
        Other:
        Acoustical studies: One condenser and one crystal microphone to measure
            meteoric impacts and acoustic noise (Temple U.)
        Phototube experiment: Six multiplier phototubes and associated filters and
            circuits were located in Zone C of the warhead; they were mounted in groups
            of three near doors on opposite sides of warhead (AFCRC), Project No. 67
            (Aero-Medical Lab., WPAFB)
    Solar radiation: Soft x-ray study - a number of packets, each containing photographic
        film with a stepped-wedge type aluminum filter, were placed on surface of war-
        head, missile body, and fins (AFCRC)

ROCKET PERFORMANCE INSTRUMENTS

    Beacon triangulation studies: System used to obtain an accurate trajectory. Air-
        borne 470-493.5 Mc beacon transmits range pulses to four ground stations.
        (AFCRC).

DATA RECOVERY INSTRUMENTS

    Telemeter: NRL PPM-AM telemetering system, 30 channels, transmitter type
        AN/DKT-2 (XN-1); BRL telemetering equipment (doppler) used as single
        channel
    Physical recovery: Separation at peak altitude by radio command to ARW-37 cutoff
        receiver
    Blossom IV-D nose section to be separated from missile body by means of four
        pistons actuated by an explosive charge (FILRAD, WADC)
    Parachute recovery: Parachute system consists of a red 80-ft nylon ribbon main
        canopy and a 16-ft nylon ribbon drag parachute (FILRAD, WADC)

BALLISTIC INSTRUMENTS

    Firing Range
        Theodolites: One Mitchell and four Askania stations
        Cameras: Two ballistic and three Bowen-Knapp stations
        Telescopes: Four stations
        Radar: Two modified S-band radars
        Doppler: Four stations

    Airborne
        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: 10,211 lb
    Gross weight at takeoff: 29,695 lb

ROCKET PERFORMANCE

    Program angle: Seven degrees from vertical
    Time to burnout: 64.6 sec
    Velocity at burnout: 4410 ft/sec
    Altitude at burnout: 20.1 miles
    Time to zenith: 204.5 sec
    Altitude at zenith: 81 miles
    Flight duration: 346 sec to impact
    Impact coordinates: Main body - 37.8 mi. from the launcher on azimuth of 357
        degrees 46'; warhead - about 2 mi. north of main body

BALLISTIC DATA

   Theodolites: Sketchy Askania data available after burnout until approximately 100
        sec, Mitchell data obtained from about 45 to 106 sec and at intervals earlier
    Cameras: Bowen-Knapp images for 13 sec. Ballistic - images infrequent because
        of clouds.
    Telescopes: Tracked over peak and through separation
    Radar: Good signal until 160.5 sec and from 183 sec until 219.5 sec; sporadic
        thereafter
    Doppler: Good signal received until 80 sec

DATA RECOVERY

    Telemeter: NRL telemetering system signal was good until warhead separation, at
        which time synchronizing pulse disappeared
    Physical recovery: K-25 camera was damaged, but film usable. Warhead, minus
        parachute, was in badly damaged condition.

EXPERIMENTAL DATA

    Soft x-ray study: Packets on main body of rocket severely damaged upon impact;
        packets on warhead, though recovered, damaged to extent that no data were
        obtainable
    Skin temperature: Excellent curves of temperature vs time for heating effects due
        to frictional dissipation between various points on the missile and adjacent air
        molecules
    Oblique incidence propagation experiment: Excessive interference, poor data
    Vertical incidence ionosphere propagation experiment: Intermittent operation, no
        satisfactory results
    Acoustical studies: Acoustical noise related to progress of flight; about 66 pips were
        attributed to meteoric impacts
    Phototube experiment: This experiment, as indicated by the telemetering records,
        performed very well and yields some important data on sky brightness studies
    Emission spectrum: Discharge not sufficiently diffused to produce desired spectra
    Beacon triangulation studies: Good trajectory to 61 sec, intermittent thereafter
    Luxembourg experiment: As a result of intermittent operation, insufficient data were
        obtained to realize significant results

COMMENTS

    Rocket modifications Rocket carried new elongated nose section (Blossom) which
        provides for 80 to 100 cubic feet of space for research instruments. Length of
        original V-2 ws increased by one diameter.
    Rocket performance: Takeoff was normal. Steering was good and performance of
        the propulsion unit was better than predicted.

REPORTS AND PAPERS

    "Investigation of the Ionosphere Utilizing Sounding Rockets," Upper Atmosphere
        Research Laboratory, Boston University, Contract AF19(122)-36, Report No. 3,
        31 May 1950
    "Luxembourg Equipment, Common Power Supply," Tufts College, Contract
        AF19(122)-89, Progress Report No. 2, 15 September - 15 December 1949
    "Research in the Physical Properties of the Upper Atmosphere, With Special
        Emphasis on Acoustical Studies with V-2 Rockets," Research Institute of Temple
        University, Contract W19-122 ac-12, Report No. 8, 24 May 1950