Set”
Sd
v
Waeres
rojeet-~ E.2
0 In-Plight Perticipatien of a P-52 sen
[t Francis L, Williams
CIIECTIVE
a4
uy
The cbjective of this te % was to determine the delivery capatility of the 2-52 aircraft.
INETRUMENT ATION
Instrumentation of the P-52 for Huron Shot consisted of 304 os~
stllceraph channels which recorgel mcasurements from strain~gage
bridges, atcelcrom:ters, roll and pitch gyros, radiometers, fressure
transducers, calorimeters, thermocouples, and control position transducers.
In addition, 14 cameras recorded photorecorder instruments
5
(24 channels), wing ant tail deflecticn, cloud coverage, and fireball
rise end grovth.
TAT ate
-~ wih.
THOTTTOYT
=
ee
ST
Tir
a
QAnraar
st
wt
The fellowing chart shows the atrersftts positicn at Ts) and T;?
Altitude
(2t-.ft)
Sonditfens
20,002
ffset
(*t)
Eealing
Tee)
Slant Dis-
tance (ft)
Velocity (fps)
TAS
Ground
550
110
20,800
750
750
20,009 400
110
39,€00
758
758
at Timc Zero
Sonlitions at
Shock Arrival
RTeMITS
28.6 BTU/ft” measured at BS 655 by a 160° field Calorimeter pointed
148°F measured on a 0,025 Aluminum elevator panel at ES 230.
The
—~)
absorptivity of thie panel was 0.54.
1 Porecp/COL
LaAab RC
-16-
/