Project 5.3 - In-Flight Participation of a B-66B Aircraft - R. W. Bachman
OBJECTIVE
The primary objective of this test was to measure the gust, thermal,
overpressure and high Q field effects of e high yield megaton nuclear weapon
on a B-66B aircraft.
INSTRUMENTATION
Instrumentation on the B-66B included a total of 298 recording channels
consisting of strain gages, thermocouples, accelerometers, calorimeters, one
radiometer and wing and tail deflection cameras.
Also included in the.
instrumentation were 32 besic flight instruments on a photo-recerder panel
and 8 correlation channels.
AIRCRAFT POSITION IN SPACE
Using the K-5 Radar and Raydist Positioning System, the F-66B was
positioned at an altitude of 19,000 feet on a heading of 124° with a
horizontal range of 27,250 feet at zero time.
At shock arrival time the
horizontal range was 65,900 feet with the eaircreft on the same heeding and
at the same altitude as at zero time.
RESULTS
Thermal:
Total thermal energy measured was 44 cal/en®,
Maximum AT
measured was 258°F on the 0,016 painted elevator panels, which cives a total
temperature of 322°F on the elevator.
Gust:
Maximum gust loading at shock arrival time was 1.68 g's (56%
allowable limit on the wing using a dynamic magnification factor of 1.59).
Overpressure:
Operability:
Damage:
Peak overpressure measured was 0.84 psi.
Of the 298 data recording channels, 97% were operable.
The only visual damare was the turning and delemination of the
lower quadrant of the tail radome.
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