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A three-dimensional computer code has been developed for the solid-ruei ramjet combustion process. The code includes finite-rate chemical kinetics and has been used to predict the combustion behavior for axial inlet, side-dump inlet and bypass configurations. supported by Naval Weapons Center, China Lake, California http://archive.org/details/threedimensional00mils

An experimental investigation was conducted to examine the effects of inlet air swirl and secondary gas injection on the combustion properties in a solid fuel ram jet. Tests were conducted with both HTPB and PMM fuels in order to obtain general results. The swirl tests were conducted at high and low air mass fluxes with equivalence ratios less than unity. Swirl was found effective for increasing the fuel regression rate but the magnitude was highly dependent upon motor geometry, fuel type and operating environment. The gas injection tests included hydrogen at low equivalence ratios, and nitric oxide and nitrous oxide at high equivalence ratios. Secondary injection generally resulted in increases in combustion pressure in agreement with equilibrium, adiabatic combustion expectations. http://archive.org/details/anexperimentalin1094521845 Lieutenant, United States Navy Approved for public release; distribution is unlimited.

A photographic investigation of metallized and non-metallized composite solid propellant combustion was made. Propellant strands made from large unimodal AP and PBAN binder, both with and without aluminum powder, were burned in a conventional stainless steel combustion bomb. High speed color schlieran motion pictures were taken of the combustion process to determine the effects of pressure and strand thickness on propellant deflagration. Results are discussed and compared with data on AP/binder sandwich experiments. http://archive.org/details/schlierenstudyof1094517222 Lieutenant, United States Navy Approved for public release; distribution is unlimited.

A full scale gas turbine combustor test facility was designed, constructed, and initially operated to determine the performance of a gas turbine combustor and the associated combustion diagnostic apparatus. The test cell was put through an initial series of four tests. The combustor was opera ted at 75% of normal operating conditions. A water cooled extractive probe sampling system was used to obtain a particulate sample and an optical system was used to measure the transmissivity inside the combustor and at the exhaust. The opacity of the exhaust gases was also monitored. The initial test series verified the adequacy of the test cell control apparatus as well as the extractive probe sampling systems. The optical technique employed appeared to be adequate for the purpose of determining the mean particle diameter, but lacked sensitivity for use at the engine exhaust. Recommendations were made for facility and equipment improvements. http://archive.org/details/anexperimentalin1094519806 Lieutenant Commander, United States Navy Approved for public release; distribution is unlimited.

This thesis supports computer-aided data analysis of holograms produced from rocket motor firings. The work reported in this thesis modified existing software code to make it compatible with installed upgrades in the microcomputer imaging system. In particular, this involved converting the format of C language function calls to ITEX/PC image processing software to that dictated by YTEX/FCplus software. Additional modifications were performed to enhance code portability and optimization. Results indicate that all efforts to incorporate the new system software have been successful. Air Force Astronautics Laboratory N0F04611-89-X-006 http://archive.org/details/implementationof1094527089 Air Force Astronautics Laboratory N0F04611-89-X-006 Lieutenant, United States Navy Approved for public release; distribution is unlimited.

A small, uncooled research rocket motor was built to study the effects of a vortex flow on combustion instability. Normal heptane and air were used as propellants with the air being divided into two flows; a primary flow at the center of the combustion chamber and a secondary flow at the periphery of the chamber. The secondary air provided the swirl which could be directed clockwise or counterclockwise at various angles or a straight mode of operation. Runs were made at various flow rates with the direction of swirl changed during the run. A first tangential high frequency mode of combustion instability was developed and a significant change in stability conditions was found when a vortex flow was generated within the combustion chamber. It was found that a swirl in one direction tended to decrease the instability while a flow in the opposite direction increased it. http://archive.org/details/aninvestigationo1094512423 Lieutenant, United States Navy Approved for public release; distribution is unlimited.