An account is presented of the research accomplished on each of the two phases of the contract, entitled Radiation Measurements and Reentry Flow field Analysis. Shock tube radiation measurements have been begun on air and other N2-O2 mixtures covering the wavelength range 3500 to 9500A and temperatures as low as 2500 K. The experiments are planned to determine the effects of NO2, NO and N2 in contributing to the radiation from shock-heated air. Considerable effort was expended in an attempt to eliminate what appear to be the effects of impurities in the records, which become more pronounced at lower temperatures. These studies are discussed, and preliminary results of the air species radiation experiments are presented. Recent modifications of the bow shock program developed under the present contract are described. An approximate afterbody program, utilizing a previously developed nozzle calculation, was generated during the past reportion period, and this program is also discussed briefly. An investigation of two alternate methods of calculating afterbody flows is given. One of these methods, which is adaptable to non-axisymmetric flows, is presently being programmed for the IBM 7044. (Author).

A study of the infrared emission in heated air s sumarized. The experimental apparatus for quantitative measurement of the radiated infrared energy is descri ed. The design, calibration and testing of the shock tube and a ultichannel infrared spectrometer are presented. Preliminary measurements of the radiation from nitrogen in the wavelength range from 0.95 to 1.10 microns are reported. These results clearly show the strong (0,0) and (2,2) bandheads of the nitrogen 1st positive system. Measurements of the dependence of the radiation intensity on temperature over the range studied (5700 - 7000 K) are in good agreement with predctions for this and system based on the equilibrium populions of the upper energy levels from which the transitions occur. A genel analysis of the nonequilibrium flow around re-entry vehicles is presented which consides finite-rate kinetics and includes the coupling of vibration and dissociation in the gas. The numerical techniques to be employed in the solution of the equations are discussed. (AUTHOR).

Progress in Astronautics and Rocketry, Volume 7: Hypersonic Flow Research compiles papers presented at a conference on hypersonics held at the Massachusetts Institute of Technology in August 1961. This book discusses the low Reynolds number effects, chemical kinetics effects, inviscid flow calculations, and experimental techniques relating to the problems in acquiring an understanding of hypersonic flow. The structure and composition of hypersonic wakes with attendant complex chemical kinetic effects is only briefly mentioned. This text consists of five parts. Parts A to C comprise of theoretical papers on the problems of calculating flow fields at hypersonic speeds. The experimental techniques that are of immediate practical interest in view of the difficulty of flight testing are discussed in Parts D and E. This publication is beneficial to engineers involved in advanced design problems.

The program areas included in this report are early work on the Wave Superheater and related research on Chemical Nonequilibrium in High-temperature Gas Flows, a Radiation Probe, Sound Propagation in an Excited of Dissociated Gas, Boundary Layer Phenomena in High-Temperature Gas Flows, and Molecular Interaction at High Temperatures.