Download or read book Experimental Investigation of Ramburner Performance Part I Liquid Propellant Runs written by R. A. Meese and published by . This book was released on 1972 with total page 177 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the results of a series of connected-pipe runs with an air-augmented rocket system burning liquid rocket propellants. The liquid propellant runs served to evaluate the behavior of the facility and instrumentation with regard to accuracy and to provide performance data for combustion where the chemical rate processes were relatively fast compared with those of metal combustion. The ramburner was designed to provide axisymmetric, coaxial mixing of the primary and secondary streams in a constant area duct. No mixing aids were employed. Nitrogen tetroxide and Aerozine-50 served as the rocket propellants. The secondary air was preheated by combustion to a nominal temperature of 1100 R to simulate flight stagnation conditions. Runs were made with nominal pressures in the ramburner of 90 and 175 psia. The air/propellant ratio was varied from 5 to 13 (approximately 250 to 600 percent theoretical air). Two oxidizer-to-fuel ratios were employed for the primary rocket: 0.8 (fuel rich) and 2.0 (stoichiometric). Combustion efficiencies between 75 and 90 percent were observed for the complete system, decreasing with increasing air/propellant ratio. Estimated uncertainties in the efficiency values were + or - 3 percent. Ramburner efficiencies tended to be 10 to 15 percent lower and were subject to uncertainties in the neighborhood of + or - 6 percent. A slight decrease in efficiency with decreasing pressure was also observed. (Author).
Download or read book An Experimental Investigation of the Effects of Combustion on the Mixing of Highly Reactive Liquid Propellants written by Bruce H. Johnson and published by . This book was released on 1965 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Uncooled Thrust Chamber Materials for Use in Storable Liquid Propellant Rocket Engines written by R. W. Rowley and published by . This book was released on 1964 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Baffled Tube Ram Accelerator Operational Characteristics written by Colin Hugh Hambling and published by . This book was released on 2017 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the baffled tube ram accelerator operational characteristics is presented. The ram accelerator is a novel hypervelocity launcher concept wherein a subcaliber projectile, as it travels through a stationary tube filled with a premixed fuel and oxidizer, initiates and sustains a combustion wave, generating continuous thrust. A quasi-steady, one-dimensional blackbox model is used to predict the acceleration, and thus, the thrust generation of the smooth bore thermally chocked ram accelerator propulsive mode. The baffled tube ram accelerator is a modern spin on the smooth bore ram accelerator. Designed to contain a forward surging combustion wave, the baffled tube ram accelerator permits the use of highly energetic propellants and, up to a certain degree, prevents the limiting condition of an unstart from occurring. Smooth bore ram accelerator operation is bound by three gas dynamic limits: a minimum Mach number required to keep the diffuser started, a minimum heat release required to keep the normal shock on the body, and lastly a maximum heat release beyond which the normal shock will be driven over the projectile. Due to the simple fact that the baffled tube ram accelerator is designed to expand these limits, difficulties arise when attempting to accurately predict the performance using the previously mentioned blackbox model. Prior experiments at the UW have attempted to develop a model better fit to understand operation in the baffled tube. This investigation is motivated by the need for empirical data to find correlation between performance models and experimental work, all with the intent to push the baffled tube ram accelerator closer to real-world applications. A new series of approximately 30 firings is presented to explore the unknown operational envelope of a methane/oxygen/nitrogen propellant mixture. Both entrance velocity of the projectile and heat release of the propellant were varied to map the initial experimental envelope of operation. Within the scope of this experimental investigation, the limits of the baffled tube ram accelerator running a methane/oxygen/nitrogen propellant mixture have been identified and the operational characteristics at and around these limits have been explored. Furthermore, concerns regarding the structural integrity of two-part and/or hollow projectiles were suppressed through a sub-series of experiments. This opened doors in to new possibilities for projectile design and configuration. Ultimately the results suggest the need for future work as the baffled tube ram accelerator envelope of operation has yet to be fully developed. However, the results also highlight great potential in the application of ram accelerators.***** An experimental investigation of the baffled tube ram accelerator operational characteristics is presented. The ram accelerator is a novel hypervelocity launcher concept wherein a subcaliber projectile, as it travels through a stationary tube filled with a premixed fuel and oxidizer, initiates and sustains a combustion wave, generating continuous thrust. A quasi-steady, one-dimensional blackbox model is used to predict the acceleration, and thus, the thrust generation of the smooth bore thermally chocked ram accelerator propulsive mode. The baffled tube ram accelerator is a modern spin on the smooth bore ram accelerator. Designed to contain a forward surging combustion wave, the baffled tube ram accelerator permits the use of highly energetic propellants and, up to a certain degree, prevents the limiting condition of an unstart from occurring. Smooth bore ram accelerator operation is bound by three gas dynamic limits: a minimum Mach number required to keep the diffuser started, a minimum heat release required to keep the normal shock on the body, and lastly a maximum heat release beyond which the normal shock will be driven over the projectile. Due to the simple fact that the baffled tube ram accelerator is designed to expand these limits, difficulties arise when attempting to accurately predict the performance using the previously mentioned blackbox model. Prior experiments at the UW have attempted to develop a model better fit to understand operation in the baffled tube. This investigation is motivated by the need for empirical data to find correlation between performance models and experimental work, all with the intent to push the baffled tube ram accelerator closer to real-world applications. A new series of approximately 30 firings is presented to explore the unknown operational envelope of a methane/oxygen/nitrogen propellant mixture. Both entrance velocity of the projectile and heat release of the propellant were varied to map the initial experimental envelope of operation. Within the scope of this experimental investigation, the limits of the baffled tube ram accelerator running a methane/oxygen/nitrogen propellant mixture have been identified and the operational characteristics at and around these limits have been explored. Furthermore, concerns regarding the structural integrity of two-part and/or hollow projectiles were suppressed through a sub-series of experiments. This opened doors in to new possibilities for projectile design and configuration. Ultimately the results suggest the need for future work as the baffled tube ram accelerator envelope of operation has yet to be fully developed. However, the results also highlight great potential in the application of ram accelerators.
Download or read book Experimental Investigation of Liquid Diborane Liquid Oxygen Propellant Combination in 100 pound thrust Rocket Engine written by William H. Rowe and published by . This book was released on 1949 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigations of Liquid Propellant Combustion Processes Using Streak Photography written by Richard M. Williams and published by . This book was released on 1968 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Liquid Rocket Engine Combustion Instability written by Vigor Yang and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 1995 with total page 600 pages. Available in PDF, EPUB and Kindle. Book excerpt: Since the invention of the V-2 rocket during World War II, combustion instabilities have been recognized as one of the most difficult problems in the development of liquid propellant rocket engines. This book is the first published in the United States on the subject since NASAs Liquid Rocket Combustion Instability (NASA SP-194) in 1972. Improved computational and experimental techniques, coupled with a number of experiences with full-scale engines worldwide, have offered opportunities for advancement of the state of the art. In this book, experts cover four major subject areas: engine phenomenology and case studies, fundamental mechanisms of combustion instability, combustion instability analysis, and engine and component testing. Especially noteworthy is the inclusion of technical information from Russia and Chinaa first. Engineers and scientists in propulsion, power generation, and combustion instability will find the 20 chapters valuable as an extension of prior work and as a reference.
Download or read book An Experimental Study of Detonative Combustion with Special Reference to Liquid Propellant Rocket Stability written by George Gemmell Cook and published by . This book was released on 1967 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Liquid Impact in a Model Propellant Tank written by David G. Stephens and published by . This book was released on 1965 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Theoretical and Experimental Investigation of the Feasibility of the Intermittent Ram Jet Engine Part 1 Theoretical Investigation Part 2 Experimental Investigation written by A. Kahane and published by . This book was released on 1951 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of High Burn Rate Propellant for Use in Nozzle less Boosters written by R. Farinaccio and published by . This book was released on 2000 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Unstable Combustion in Solid Propellant Rocket Motors written by Wilmot Grant Brownlee and published by . This book was released on 1959 with total page 302 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Unstable Combustion in Sold Propellant Rocket motors by W Grant Brownlee and Frank E Marble written by W. Grant Brownlee and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Study of Liquid Rocket Simulation of Solid Propellant Rocket Exhaust Characteristics written by L. JABLANSKY and published by . This book was released on 1964 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A substantial cost saving can be realized if a small liquid propellant rocket engine, using cheap propellants, can be used to screen nozzle materials for eventual use with large solid rocket motors using costly propellants. Work was completed in which the nozzle erosion experienced in a solid rocket motor using AHH propellant was simulated by a liquid propellant engine using white fuming nitric acid and benzene. The work was conducted at a one-to-one scale ratio and the approach taken was to simulate erosion by simulating nozzle environment. Approximate simulation of nozzle erosion was achieved. Additional work is recommended to perform simulation of aluminized propellants and study scaling effects. (Author).
Download or read book The Power for Flight written by Jeremy R. Kinney and published by Government Printing Office. This book was released on 2018-02-15 with total page 318 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NACA and aircraft propulsion, 1915-1958 -- NASA gets to work, 1958-1975 -- The shift toward commercial aviation, 1966-1975 -- The quest for propulsive efficiency, 1976-1989 -- Propulsion control enters the computer era, 1976-1998 -- Transiting to a new century, 1990-2008 -- Toward the future
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1981 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Fundamentals of Aircraft and Rocket Propulsion written by Ahmed F. El-Sayed and published by Springer. This book was released on 2016-05-25 with total page 1025 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book provides a comprehensive basics-to-advanced course in an aero-thermal science vital to the design of engines for either type of craft. The text classifies engines powering aircraft and single/multi-stage rockets, and derives performance parameters for both from basic aerodynamics and thermodynamics laws. Each type of engine is analyzed for optimum performance goals, and mission-appropriate engines selection is explained. Fundamentals of Aircraft and Rocket Propulsion provides information about and analyses of: thermodynamic cycles of shaft engines (piston, turboprop, turboshaft and propfan); jet engines (pulsejet, pulse detonation engine, ramjet, scramjet, turbojet and turbofan); chemical and non-chemical rocket engines; conceptual design of modular rocket engines (combustor, nozzle and turbopumps); and conceptual design of different modules of aero-engines in their design and off-design state. Aimed at graduate and final-year undergraduate students, this textbook provides a thorough grounding in the history and classification of both aircraft and rocket engines, important design features of all the engines detailed, and particular consideration of special aircraft such as unmanned aerial and short/vertical takeoff and landing aircraft. End-of-chapter exercises make this a valuable student resource, and the provision of a downloadable solutions manual will be of further benefit for course instructors.
