Download or read book Data Base for the Prediction of Airframe propulsion System Interference Effects written by and published by . This book was released on 1979 with total page 444 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Modern Engineering for Design of Liquid Propellant Rocket Engines written by Dieter K. Huzel and published by AIAA. This book was released on 1992 with total page 452 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Advances in Cryogenic Engineering written by K.D. Timmerhaus and published by Springer Science & Business Media. This book was released on 2013-12-14 with total page 591 pages. Available in PDF, EPUB and Kindle. Book excerpt: The 1961 Cryogenic Engineering Conference Committee is pleased to present the papers of the 1961 Cryogenic Engineering Conference. We are grateful to have had the University of Michigan at Ann Arbor, Michigan as our host for the seventh annual meeting of this group. The Conference Committee in presenting the papers oftbis Conference takes this opportunity to acknowledge the assistance of an Editorial Committee in the selection of papers for the program. Since over one hundred and twenty papers were submitted, their task of screening and evaluating the papers was a dif ficult one. The Committee guided by G. j. V an Wylen, who also served as chair man of the Conference Committee, included R. W. Arnett, B. W. Birmingham, D. B. Chelton, R. j. Corruccini, C. j. Guntner, M. j. Hiza, R. B. jacobs, A. J. Kidnay, R. H. Kropschot, j. Macinko, D. B. Mann, R. P. Mikesell, R. L. Powell, J. R. Purcell, R. P. Reed, R. j. Richards, A. F. Schmidt, R. B. Stewart, and K. A. Warren.

Download or read book Cryogenic Engineering written by Klaus D. Timmerhaus and published by Springer Science & Business Media. This book was released on 2007-11-12 with total page 379 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is a benchmark reference work on Cryogenic Engineering which chronicles the major developments in the field. Starting with an historical background, this book reviews the development of data resources now available for cryogenic fields and properties of materials. It presents the latest changes in cryopreservation and the advances over the past 50 years. The book also highlights an exceptional reference listing to provide referral to more details.

Download or read book Cryogenic Properties written by A. J. Kidnay and published by . This book was released on 1986 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Performance of Convergent and Plug Nozzles at Mach Numbers from 0 to 1 97 written by Douglas E. Harrington and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Design and Tuning of Competition Engines written by Philip Hubert Smith and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Nozzle Lateral Spacing on Afterbody Drag and Performance of Twin jet Afterbody Models with Convergent Nozzles at Mach Numbers Up to 2 2 written by Donald L. Maiden and published by . This book was released on 1970 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Plastically Crystalline State written by John Neil Sherwood and published by John Wiley & Sons. This book was released on 1979 with total page 424 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Note on Performance of Aircraft Ejector Nozzles at High Secondary Flows written by Fred D. Kochendorfer and published by . This book was released on 1954 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Jet Velocity and Axial Location of Nozzle Exit on the Performance of a Twin jet Afterbody Model at Mach Numbers Up to 2 2 written by Bobbly Lee Berrier and published by . This book was released on 1969 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Plug and Shroud Geometry Variables on Plug nozzle Performance at Transonic Speeds written by Bobby L. Berrier and published by . This book was released on 1969 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Static Thrust of an Annular Nozzle with a Concave Central Base written by Blake W. Corson (Jr) and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A static test of an annular nozzle with a concave central base, producing a jet in which tangents to the jet streamlines at the exit converged toward a region on the axis of symmetry downstream of the exit, has indicated good thrust performance. A value of nozzle-flow coefficient only slightly less than unity indicates the internal loss to be small. Pressures on the concave central base are relatively large and positive, and a predictable portion of the total thrust of the jet is exerted on the central base.

Download or read book An Investigation of F 16 Nozzle afterbody Forces at Transonic Mach Numbers with Emphasis on Support System Interference written by Earl A. Price (Jr.) and published by . This book was released on 1979 with total page 416 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive experimental program was conducted to provide nozzle-afterbody data with a minimum interference support system on a 1/9-scale F-16 model and to determine the interference induced on the afterbody-nozzle region by a sting, a wingtip, and a strut model support system. The investigation was conducted over the Mach number range from 0.6 to 1.5 and at angles of attack from 0 to 9 deg. Interference was evaluated by comparison of nozzle-afterboy axial and normal forces obtained from integrating pressure data. The results include parametric studies of the efects of various components of the wingtip support system (i.e., the support blade axial position, wingtip boom diameter, boom spacing, and boom-tip axial location). High-pressure air at ambient temperature was utilized for exhaust plume simulation. The results indicate that a sting support passing through the nozzle with the jet effects simulated by an annular jet appears to offer a minimum interference support system for the type of nozzle-afterbody test described in this report.

Download or read book Comparison of Simplex and Dual orifice Fuel Nozzles with Ambient and Heated Fuel in an Annular Turbojet Combustor written by Donald F. Schultz and published by . This book was released on 1971 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A full-scale annular combustor was operated with simplex fuel nozzles of three flow ranges and with dual-orifice fuel nozzles. The dual-orifice nozzles provided combustion efficiencies within 2 to 3 percent of the peak values obtained with any of the simplex atomizers. A wide range of operating conditions including altitude relight, simulated takeoff, Mach 2.7 cruise, and Mach 3.0 cruise were studied. Measurements were made of combustion efficiency, pattern factor , flame radiation, smoke emission, and response to rapid increase in fuel flow. Fuel heated to 300 [degree] F (423 K) was used in many of the tests; heated fuel usually increased combustion efficiency.

Download or read book Performance of Twin dimensional Wedge Nozzles Including Thrust Vectoring and Reversing Effects at Speeds Up to Mach 2 20 written by Francis J. Capone and published by . This book was released on 1977 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range written by C. E. Robinson and published by . This book was released on 1974 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an experimental and analytical research investigation on nozzle/afterbody drag are presented. Experimental afterbody (and boattail) drag coefficients and pressure distributions are discussed for an isolated, strut-mounted nozzle/afterbody model for the Mach number range from 0.6 to 1.5. Some data are also given for free-stream unit Reynolds numbers from one million to approximately four million per foot. The experimental data were obtained for the basic model with an air-cooled and a water-cooled Ethylene/air combustor to provide hot-jet duplication as well as cold-jet simulation. The temperature of the nozzle exhaust gas was varied from 530R (burner-off) to approximately 2500R for several nozzle pressure ratios from jet-off to those corresponding to a moderately under-expanded exhaust plum. The initial series of experiments was conducted with the air-cooled combustors, and the effect of jet temperature on afterbody drag was somewhat masked by the effects of the secondary airflow from the cooling air. The general trend, however, shows a decreasing afterbody drag with increasing exhaust gas temperature and with decreasing secondary airflow at a fixed nozzle pressure ratio. (Modified author abstract).