wa SNS aboard the U.S.S. Estes; hence no radar track data wore obtained. No 4.2.2 ate te . Se mo reliable overpressure data were obtained from instrumentation aboard the aircraft, primarily because of the low input level. ee The position quoted is based upon calculations using time of shock arrival and upon crew estimate, At shock arrival the aircraft was out of range for the radar So ® Eesell The wide discrepancy is at- tributed to the failure of the "K" system radar. by . sae NS na aes sy ‘, ee a Se ee ete ete ad The sircraft position at shock arrival was 28,000 ft farther from ground zero than originally planned. B47 Aircraft Data, other than response measurements, pertinent to the exposure . of the Bei,7 aircraft in King Shot are summarized below: d. Slant range at shock arrival, 42,760 ft g True heading, 68° 6. f. h. 4. True airspeed, 440 mots True ground speed, 412 knots Aircraft attitude, 1° nose high Angle of incidence of shock front, 51.4° j. Shock arrival time, 32,2 sec 1. Gross weight at shock arrival, 120,000 lb k. 4.3 Height of Burst, 1500 ft Horizontal range at shock arrival, 26,€00 ft , mere b. ce. ere a. Altitude, MSL, 35,000 ft £ Peak overpressure (AFCRC), 0.336 psi. RESPONSE MEASUREMENTS Measurements made on the blast response of the B~36 and B-47 aim craft in King Shot are presented in the sub-paragraphs below. All data are presented as time-histories with only the obvious, small amplitude oscillations faired out. The time axis is based upon time of shock ar~ rival et the tail. To obtain time relative to burst time; for the B36 aircraft add 77.2 sec; for the 5-47 aircraft add 32,2 sec, of the horizontal stabilizer was only 12 per cent of limit load, 4.3.1.1 Bending Moment sending mement measurements are presented in terms of tending moment above, or celow, normal (one ¢) fligitt loads, Wing, fuselare, and horizontal steacilizer bending measurememts are presented in Figs. 4.2 through 4.7. «cceptahle results were octaimed from all bending pages, except the root ce:cing vage on the lef. wimg. This gage was found ine weet, pecause the 3-26 aircraft was too far from air zero on this shot, the forcing functions, ard therefore the measured loads, were lower than anticipated, The data are of values however, their utility in checking the plast-load theory would have been greatly enhanced had the responses been several-fold higher. The peak measured bending moment OAM ‘ B36 Aircraft vote 4.3.1