1100 one perhaps observed a different type of degradation, as the blast weve passed from “shock” to sonic amplitudes. rE When the shock wave becomes very 3 week, ite velocity as well as sound velocity behind it approaches ambient sound velocity. If the wave form is perturbed, because of either surface or atmospheric effects, it is virtually impossible for the wave to "shock up’ S again, hence the long rise times vhich appear at Runit and Parry. Further data will de available from mass motion studies, afterwind F E studies and cannister ea <aT ava AILABLE COPY 4 fines of arrival are available from Sandia Corporation's mesurenents in Project 6.1, and from measurements aboard the Estes by Cowan ani Reines ' z (altimeter and stop-watch) and by England (Wiancko gauge with brush recorder). :, scan’ wave furnish a rough estimate of yield and some insight into the hyéro- i A theoretical, tine of arrival curve consistent with the theoretical yeak . of tha blast wave. This shows small, if at all, significant differences from E The difference in tine between sheck arrival and the computed arrival of 's pressure - distence curve of Table I is available from a machine calculation the tineof arrival curve of Figure 7, J-19372, which was calculated originally from early tests of ataxio weapons. Based on the theoretical curve and com puted sound velooity at the surface, the apparent yielés are: i 4 Distance locstion «=—-s«=L(Feet), Parry tee Eates Runit Aomon. Aitsu Masin Rngedi 18%,000 Sound fhock Velocity Arrival ‘ Tine (vs) (Secomis}) Differences W_(0) 4396 85.3 we a 28.76 13.3 10.0 30 > 14.9 j 47,600 51.2 ask 36,700 £1,400 Liss List 15,900 19. 35 8.7 1125 9.3 aXd jel : Pe “eyoeSas Satygad. fe ‘ 13.3 10.35 3 10.3. . 12.5 9 8.5 SNL ~5a 19.0 4 akk a rane am E :