Sounding rockets
Sounding rockets for transporting scientific instruments in nearly vertical trajectory
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Sounding rockets for transporting scientific instruments in nearly vertical trajectory
Turbopump feed systems for hydrogen nuclear rockets
Turbopumps for liquid propellant rocket engines
Application and extension of modern automatic control theory to nuclear rocket dynamics and control
Thermodynamic properties of coolant fluids and particle seeds for gaseous nuclear rockets
Lunar photographs transmitted by multistage rocket vehicle
Lateral and longitudinal combustion-pressure oscillations that occurred in screaming combustion of a 1000-pound-thrust rocket engine using white fuming nitric acid and JP-4 fuel as propellants were successfully prevented by means of longitudinal fins in the combustion chamber. Fin position was critical, and complete attenuation was achieved only when the fins were located in a zone approximately 8 to 16 inches from the injector. Fins located in other zones, that is, near the injector or far downstream from the injector, did not stop the oscillations. When oscillations occurred in finned chambers, the longitudinal mode seemed more dominant than the lateral mode; in chambers without fins, the lateral mode tended to be dominant. The lateral oscillation was distorted and its intensity diminished by the fins. Fins, however, did not affect the frequencies; the longitudinal frequency varied inversely with chamber length, and lateral frequencies varied only slightly from an average of 6000 cycles per second.
Flight performance, shock, and vibration data from Scout launch vehicle X-258 rocket engine
Turbulent boundary layer heat transfer from fast accelerating flow of rocket exhaust gases and heated air
Bipropellant rocket engines with radiation cooled thrust combustion chambers of molybdenum fired for testing and material evaluation
Rocket measurements of cosmic radio noise intensities below five Mc/s
Model for prediction of rocket engine combustion with performance parameters of gas phase turbulent diffusion, and mixing of oxidizer and fuel vapors
Heat transfer measurements on blunt spherical segment nose and cylindrical body and flight test of rocket-propelled model
Separation of jettisonable-nose pilot-escape capsule investigation by means of rocket-model flight tests
Force measurement and weighing problems in rocket and space vehicles - NASA speech
Dynamic structural behavior of large booster rocket subjected to longitudinal excitations - analysis of theoretical model
Mesosphere structure and dynamics during quiet sun period from rocket observations