Download or read book Evaluation of Various Exhaust Nozzles at Free stream Mach Numbers from 0 6 To 3 0 written by Lawrence L. Galigher and published by . This book was released on 1970 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Evaluation of Various Exhaust Nozzles at Free stream Mach Numbers from 0 6 To 3 0 written by Lawrence L. Galigher and published by . This book was released on 1970 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 994 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Evaluation of Boattail Geometry and Exhaust Plume Temperature Effects on Nozzle Afterbody Drag at Transonic Mach Numbers written by L. L. Galigher and published by . This book was released on 1976 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted to investigate the interaction effects which occur between the nozzle exhaust flow and the external flow field associated with isolated nozzle afterbody configurations at transonic Mach numbers. Pressure data were obtained from three afterbody geometries with boattail angles of 10, 15, and 25 deg at Mach numbers from 0.6 to 1.5 at zero angles of attack and sideslip. Cold (High-pressure air) and hot (Air/ethylene combustion) jet test techniques were used to simulate and duplicate, respectively, the nozzle exhaust flow for a sonic jet installation. Nozzle exhaust temperature was varied from 540 to approximately 2,900 R. The most significant results pertain to those effects on boattail pressure drag caused by exhaust plume temperature and flow asymmetry (Model support strut induced). The differences obtained in boattail pressure drag between the cold jet simulation and hot jet duplication results were significant at nozzle pressure ratios representative for turbofan and turbojet engines at subsonic Mach numbers. Adjusting the cold jet nozzle pressure ratio to correct for changes in the exhaust plume specific heat ratio with temperature did not account for the differences observed. Flow asymmetry effects were Mach number and nozzle pressure ratio dependent and increased in severity as the boattail angle was increased.
Download or read book Characteristics of Five Ejector Configurations at Free stream Mach Numbers from 0 to 2 0 written by John L. Klann and published by . This book was released on 1959 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pitot Survey of Exhaust Flow Field of a 2 D Scramjet Nozzle at Mach 6 with Air Or Freon and Argon Used for Exhaust Simulation written by William J. Monta and published by . This book was released on 1992 with total page 40 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 NASA Technical Note written by and published by . This book was released on 1972 with total page 798 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Reference Publication written by and published by . This book was released on 1977 with total page 116 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 Thrust Performance of Isolated Plug Nozzles with Two Types of 40 spoke Noise Suppressor at Mach Numbers from 0 to 0 45 written by Douglas E. Harrington and published by . This book was released on 1974 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Plug nozzles with two types of 40-spoke noise suppressor were tested at free-stream Mach numbers from 0 to 0.45 and over a range of nozzle pressure ratios from 1.5 to 4.0. In addition, an unsuppressed plug nozzle and a Supersonic Tunnel Association nozzle were also tested to provide baseline levels of thrust performance. The unsuppressed plug nozzle had an efficiency of 98 percent at an assumed takeoff pressure ratio of 3.0 and at Mach 0.36. At the same condition the suppressor nozzles had efficiencies of approximately 83.5 percent.
Download or read book Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0 45 written by Douglas E. Harrington and published by . This book was released on 1976 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book APSI Advanced Exhaust Nozzle Test Results at Mach Numbers from 0 6 to 1 5 written by Ernest J. Lucas and published by . This book was released on 1979 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test program was conducted in the Propulsion Wind Tunnel to obtain force and moment and surface pressure data on a 0.096-scale model of a proposed tactical aircraft. The force data were acquired with two separate internal balances, which measured the aircraft and the nozzle thrust-minus-drag loads, respectively. Results were obtained for two axisymmetric and four nonaxisymmetric nozzles at three simulated power settings. Nozzle deflections were simulated to define the change in maneuverability to be gained by vectoring the simulated exhaust jet. In addition to the simulated powered configurations, an open inlet flow-through reference configuration was tested to determine the basic airframe aerodynamics with forward and aft wing placements. The tests were conducted at Mach number from 0.6 to 1.5 at a free-stream Reynols number of 2.5 million/ft. Angle of attack was varied from -1 to 16 deg at nozzle pressure ratios from 1.0 (jet-off) to 20. (Author).
Download or read book Thrust Performance of Isolated 36 chute Suppressor Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0 45 written by Douglas E. Harrington and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance of an Auxiliary Inlet Ejector Nozzle with Fixed Inlet Doors and Triple hinge Trailing edge Flap written by Albert L. Johns and published by . This book was released on 1970 with total page 76 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).
Download or read book Annual Report written by National Aeronautical Laboratory (India) and published by . This book was released on 2006 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
