presented for the wings, fuselage, and horizontal stabilizers in Fig. 3.2 through Fig. 3.6# The first 0.15 sec after shock arrival are shown as a dashed line for the bending moment of the left horizontal stabilizer, Fig. 3.8, because the trace could not be followed continuously through this interval. All bending gages yielded acceptable results. 3.3.2 | Acceleration Tail, nose, and center of gravity acceleration records are presented in Fig. 3.9, Fig. 3.10, and Fig. 3.11, respectively. The wing tip accelerometer provided no usable data. Because of the wide, rapid fluctuations of the acceleration traces at shock arrival, the traces could not beread with any degree of accuracy until 0.4 sec had elapsed. These curveshave not been faired, although some fairing is indicated for certain analyses. 3.3.3 , . Shear and Torsion No shear or torsion data were obtained. The shear gage was inoperative prior to the test. The torsion gage output was recorded, but the data obtained were not reliable. ACTUAL POSITION AT SHOCK ARRIVAL @ UFTEMDED POSITION Af SHOCK ARRIVAL -~-- DATED TRAC —— scwal Tacx B36 3-47 DRTEWURD POS. ACTUAL POS. INTENDED POS. ACTUAL POS, HORIZONTAL RANGE 134 ,000' 127, 100! 178,550" 222,400! SLAF? RANGE 240 ,000' 2,800! 181, 8! 22 ,100' ALTITUDE 40,000! 34,500' 35,000" 35,000!