Download or read book Afterbody Drag Investigation of a Twin nozzle Fighter type Model at Mach Numbers from 0 6 to 1 5 written by Earl A. Price (Jr.) and published by . This book was released on 1972 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Afterbody Drag Investigation of a Twin nozzle Fighter type Model at Mach Numbers from 0 6 to 1 5 written by Earl A. Price (Jr.) and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Afterbody Nozzle Pressure Distributions of a Twin Tail Twin Engine Fighter with Axisymmetric Nozzles at Mach Numbers from 0 6 to 1 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-23 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt: Distributions of static pressure coefficient over the afterbody and axisymmetric nozzles of a generic, twin-tail twin-engine fighter were obtained in the Langley 16-Foot Transonic Tunnel. The longitudinal positions of the vertical and horizontal tails were varied for a total of six aft-end configurations. Static pressure coefficients were obtained at Mach numbers between 0.6 and 1.2, angles of attack between 0 deg and 8 deg, and nozzle pressure ratios ranging from jet-off to 8. The results of this investigation indicate that the influence of the vertical and horizontal tails extends beyond the vicinity of the tail-afterbody juncture. The pressure distribution affecting the aft-end drag is influenced more by the position of the vertical tails than by the position of the horizontal tails. Transonic tail-interference effects are seen at lower free-stream Mach numbers at positive angles of attack than at an angle of attack of 0 deg. Wing, David J. Langley Research Center NASA-TP-3509, L-17438, NAS 1.60:3509 RTOP 505-59-30-04...
Download or read book Parametric Study of Afterbody nozzle Drag on Twin Two dimensional Convergent divergent Nozzles at Mach Numbers from 0 60 to 1 20 written by and published by . This book was released on 1986 with total page 272 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1976 with total page 584 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Afterbody Geometry on Aerodynamic Characteristics of Isolated Nonaxisymmetric Afterbodies at Transonic Mach Numbers written by Linda S. Bangert and published by . This book was released on 1992 with total page 272 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Afterbody nozzle Pressure Distributions of a Twin tail Twin engine Fighter with Axisymmetric Nozzles at Mach Numbers from 0 6 to 1 2 written by David J. Wing and published by . This book was released on 1995 with total page 220 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 Evaluation of the Twin Nozzle afterbody Drag and Nozzle Internal Performance Computer Deck with ESIT Free Jet Data written by Phillip C. Everling and published by . This book was released on 1974 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by and published by . This book was released on 1995 with total page 218 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page 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 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1976 with total page 562 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Method for Correcting Nozzle Afterbody Drag for the Effects of Jet Temperature written by W. L. Peters and published by . This book was released on 1981 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this investigation was to isolate those parameters defined as jet mixing effects on afterbody drag in an effort to develop a method of correcting or simulating the effects of jet temperature in wind tunnel experiments. Data used in the investigation were obtained from experiments conducted in the AEDC Aerodynamic Wind Tunnel (1T) with a strut-mounted model at free-stream Mach numbers from 0.6 to 1.2. Integrated afterbody pressure drag coefficient data were acquired for three nozzle area ratios (1.0, 1.24, and 2.96) using various unheated jet exhaust gas compositions that allowed a variation in gas constant from 55 to 767 ft/lbf/lbm-deg R. Jet mixing effects on afterbody drag coefficient produced by varying jet gas constant and nozzle area ratio at nozzle design pressure ratio, and the drag effects resulting from variations in nozzle pressure ratio at certain overexpanded jet conditions were observed to be similar functions of mass flux ratio. A simple experimental method has been proposed to allow corrections of afterbody drag coefficient data obtained in the wind tunnel (using an ambient temperature air jet) for the effects of jet gas constant. By inference, a similar drag correction can be obtained for the combined effect of gas constant and temperature, assuming their product defines the effects on drag produced by variations in either property. (Author).
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1970 with total page 796 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).
