No abstract

No abstract

For air, /* = 1.64 X 10~4, ft = ^} C v = 0.1689, C P = 0.2375, 7 = 1.66, p = 1.13 X 10~3 approximately at 40°C., and g = 981; therefore, a = 1.74 X 10~3. Since m should be< a, i.e., u 0 < 1.53935 cm/sec., then X = 3.15(1.53935-u 0 ); since a small value of X is desirable, U Q should be very close to 1.53935, but should not exceed it. Therefore, the initial motion at K = 0 admissible under this solution is very slow. For a different value of UQ, T Q and p 0 = 1.3 X 10~3. The values of u m and T^ are given in Table 1., and T 7 * is plotted against K for different values of X in case I, case II, and case III (see Fig. 1).At higher temperature, p is much smaller, and we can take U Q greater than that in the preceding case. Also, if we consider a column of gas on a planet or a star where g is large and p is small, UQ can be taken much larger. References 1 Morduchow, M. and Libby, P. A., "On a complete solution of the one-dimensional flow equations of a viscous, heat-conducting compressible fluid/'

A study was made to determine the level and extent of contamination of the lunar surface that will be caused by rocket exhaust gas during the Apollo mission landing and to determine whether the contaminants will be present in lunar surface samples to be returned to earth for analysis. Water, N2, H2, and CO were found to constitute over 90 mole % of the exhaust, with CO2, H, and OH also present. Traces of organic substances may arise from thermal decomposition of phenolic materials in the rocket liner. The values of the flux density of exhaust gas impinging on the surface were estimated, and, from probable values of adsorption and desorption rates for the principal species in the exhaust interacting with the lunar surface, the spatial distribution of adsorbed contaminants was calculated. Since sample collection will not begin until about 2 hours after touchdown, the estimated desorption rates indicate that water, N2, and OH are the principal exhaust species that may remain adsorbed long enough to produce appreciable contamination, which will be heaviest along the LM approach trajectory. Maps are given for the distribution of these contaminants in the vicinity of the touchdown site.

No abstract