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Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
An experimental investigation was conducted to determine the feasibility and practicality of the dual chamber rocket concept. Cold flow studies were performed which utilized a telescoping booster cavity. The effects of booster cavity length, booster cavity shockdown pressure, booster/sustainer nozzle area ratio, and aft nozzle removal on thrust and the booster cavity pressure distribution were explored. (Author).
Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
An experimental investigation was conducted to determine the feasibility and practicality of the dual chamber rocket concept. Cold flow studies were performed which utilized a telescoping booster cavity. The effects of booster cavity length, booster cavity shockdown pressure, booster/sustainer nozzle area ratio, and aft nozzle removal on thrust and the booster cavity pressure distribution were explored. (Author).
Author: James Francis McFillin (Jr) Publisher: ISBN: Category : Aeronautics Languages : en Pages : 48
Book Description
An experimental investigation was conducted to determine the feasibility and practicality of the dual chamber rocket concept. Cold flow studies were performed which utilized a telescoping booster cavity. The effects of booster cavity length, booster cavity shockdown pressure, booster/sustainer nozzle area ratio, and aft nozzle removal on thrust and the booster cavity pressure distribution were explored. (Author).
Author: James Francis McFillin Publisher: ISBN: Category : Rocket engines Languages : en Pages : 47
Book Description
An experimental investigation was conducted to further determine the operating characteristics of the dual chamber rocket motor. Axisymmetric and two-dimensional apparatuses were used with air flow to simulate the actual flow. Without special design considerations the sustainer exhaust was found to always shockdown within the booster cavity except for very short booster lengths. Thrust was found to be insensitive to booster cavity length. With nozzle throat area ratios and booster diameters sized properly supersonic flow could be maintained within the booster cavity. Practical designs for actual motors appear quite feasible, especially for a nozzleless booster.
Author: John E. Dalgleish Publisher: ISBN: Category : Aeronautics Languages : en Pages : 20
Book Description
Experiments have been conducted with a jacketed rocket combustion chamber that was fabricated by hydraulic forming from sheet metal. Rocket combustion chambers made by this method have been used successfully. Runs with these combustion chambers have been made at over-all heat-transfer rates of 2.5 Btu per square inch per second with water cooling and also the ammonia as a regenerative coolant.
Author: John E. Dalgleish Publisher: ISBN: Category : Rockets (Aeronautics) Languages : en Pages : 11
Book Description
Experiments have been conducted with a jacketed rocket combustion chamber that was fabricated by hydraulic forming from sheet metal. Rocket combustion chambers made by this method have been used successfully. Runs with these combustion chambers have been made at over-all heat-transfer rates of 2.5 Btu per square inch per second with water cooling and also the ammonia as a regenerative coolant.
Author: G. R. Johnson Publisher: ISBN: Category : Languages : en Pages : 99
Book Description
The investigation was divided into two phases: (1) the selection and calibration of a suitable probe and (2) pressure and velocity measurements within the chamber of the cold-flow apparatus. A five-port impact tube probe was selected and calibrated. The three-dimensional calibration scheme employed for the subject investigation did not require the probe to be rotated once positioned within the rocket motor chamber. Experiments were conducted in the rocket motor chamber when a 1.125 inch throat diameter nozzle and a 2.0 inch throat diameter nozzle were employed. Pressure and velocity profiles were measured at two longitudinal locations within the chamber for rotational speeds of 1000, 3000 and 5000 rpm. The measured axial and tangential velocity profiles were compared with the predicted axial and tangential velocity profiles which were based upon a uniform axial velocity injection and a solid body vortex. (Author).
Author: W. H. Shafer Publisher: Springer Science & Business Media ISBN: 1475757859 Category : Science Languages : en Pages : 307
Book Description
Masters Theses in the Pure and Applied Sciences was first conceived, published, and dis seminated by the Center for Information and Numerical Data Analysis and Synthesis (CINDAS) * at Purdue University in 1957, starting its coverage of theses with the academic year 1955. Beginning with Volume 13, the printing and dissemination phases of the ac tivity were transferred to University Microfilms/Xerox of Ann Arbor, Michigan, with the thought that such an arrangement would be more beneficial to the academic and general scientific and technical community. After five years of this joint undertaking we had concluded that it was in the interest of all concerned if the printing and distribution of the volume were handled by an international publishing house to assure improved service and broader dissemination. Hence, starting with Volume 18, Masters Theses in the Pure and Applied Sciences has been disseminated on a worldwide basis by Plenum Publishing Corporation of New York, and in the same year the coverage was broadened to include Canadian universities. All back issues can also be ordered from Plenum. We have reported in Volume 24 (thesis year 1979) a total of 10,033 theses titles from 26 Canadian and 215 United States universities. We are sure that this broader base for theses titles reported will greatly enhance the value of this important annual reference work. While Volume 24 reports these submitted in 1979, on occasion, certain universities do report theses submitted in previous years but not reported at the time.
Author: 
Author: 
Author: James Francis McFillin (Jr)
Author: James Francis McFillin
Author: John E. Dalgleish
Author: John E. Dalgleish
Author: Leonard V. Clark
Author: G. R. Johnson
Author: 
Author: W. H. Shafer
Author: Defense Documentation Center (U.S.)