stcar gagewas drifting, producing unreliable readings and an acceleroneter went ealy off the paper and was unreadable, although functioning properly. fisctton cemsra jesacd and prodiced no results, One wing de- The photo panel camera, record- jing 26 paransters, vibrated excessively at shock arrival and five franes (.312 ) were unreadable. It is felt that no data was lost hevever, since the inslresent was not sensitive enough to react in e312 sec onds, 3. Gust Data: Overpressure measured was 75 psi. }Q percent of design limit load on the stabilator. Gust response was about Based on the ennounced yield, the responses were generally less than would have been expected. This indicates some conservatism in the selected position, lL, Thermal Data: Thermal response was considerably less than vf A T averesing 50°F on the honeycoab surfaces was recorded; this can be eh par Based on the measured inmits, the tc perature rises -C-'y ad om the critical componects vcore about 15 pt.cent Jow, “its elso tut 4 toa GT of 20°F expected, vates tene conservetisna in the selected position. vadtation: A rceding of .585 RaM was taken froa the pilot's s33se and can be cowpsared to a ,81 REM prediction based oa the eeu end position. 6. Again, some conservatism is indicated. Gsnereal: ovoject. The participstion was considered highly successful by this The responses reco:ded were of sufficient c-agnitude to serve as a U2 is es - for a re-positioning of the aircraft on further shets, OY SCUSSTON Tne combents of this postshot report are prelicinary, collected, They are subject to change pending further evaluation of the deta They were reported at this time to provide early test rosults to those concerned with effects of muclear weapons, . ok /OOE ~ 52- SS 2 oO approximate, ive and L