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- /