Download or read book Jet Effects on the Boattail Axial Force of Conical Afterbodies at Subsonic and Transonic Speeds written by William B. Compton and published by . This book was released on 1970 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Jet Effects on the Boattail Axial Force of Conical Afterbodies at Subsonic and Transonic Speeds written by and published by . This book was released on 1970 with total page 118 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 920 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Jet Effects on the Drag of Conical Afterbodies at Spersonic Speeds written by William B. Compton and published by . This book was released on 1972 with total page 60 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 1980 with total page 104 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 1980 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Fineness Ratio on Boattail Drag of Circular arc Afterbodies Having Closure Ratios of 0 50 with Jet Exhaust at Mach Numbers Up to 1 30 written by David E. Reubush and published by . This book was released on 1973 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to determine the effect of fineness ratio on the drag of circular-arc boattails at subsonic and low supersonic speeds. The boattails had closure ratios of 0.50 and incorporated convergent nozzles. The investigation was conducted statically and at Mach numbers from 0.40 to 1.30 at 0 deg angle of attack with jet total-pressure ratios varying from jet off to about 6, depending on Mach number. Low-fineness-ratio boattails had large separated-flow regions and the highest drag at all Mach numbers. Subsonic pressure-plus-friction drag levels were generally similar for boattails which did not have large separated regions. Drag-rise Mach number increased as boattail fineness ratio increased.

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1982 with total page 1282 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Download or read book Effect of Jet Convergence Angle on the Performance of Annular Nozzles with Semitoroidal Concave Plugs at Mach Numbers Up to 1 82 written by Charles E. Mercer and published by . This book was released on 1972 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an investigation at static conditions and at Mach numbers up to 1.82 are presented for 12 nozzle configurations which have jet convergence angle and jet throat area as geometric parameters. The variation of jet convergence angle from 15 to 40 deg had little effect on the performance of the nozzles having the large value of primary throat area; however, increasing jet convergence angle generally had an adverse effect on performance of the nozzles having the smaller value of primary throat area. The performance of the nozzle configurations with the larger primary throat area is competitive with nozzles designed for operation over the Mach number range.

Download or read book Support Interference of Wind Tunnel Models written by Marie H. Tuttle and published by . This book was released on 1981 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Nonlifting Empennage Surfaces on Single engine Afterbody nozzle Drag at Mach Numbers from 0 5 to 2 2 written by Bobby L. Berrier and published by . This book was released on 1977 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of Convergent divergent Nozzles Applicable to Reduced power Supersonic Cruise Aircraft written by Booby L. Berrier and published by . This book was released on 1980 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of Convergent divergent Nozzles Applicable to Reduced power Supersonic Cruise Aircraft written by Bobby L. Berrier and published by . This book was released on 1980 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Interference Between Exhaust System and Afterbody of Twin engine Fuselage Configurations written by Jack F. Runckel and published by . This book was released on 1974 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960 with total page 448 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Mass Injection and Jet Flow Simulation Effects on Transonic Afterbody Drag written by Wladimiro Calarese and published by . This book was released on 1978 with total page 184 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation has been performed to determine the effects of boattail injection and jet flow simulation on the afterbody drag of a slender body of revolution in the transonic regime at zero angle of attack, such as engine nacelles and boattailed afterbodies with isolated engines. A correlation between sting and jet diameter has been established. The jet plume and the nozzle pressure ratio simulators have been found appropriate and useful as a testing technique. Boattail mass injection usually produces a drag coefficient reduction and is more effective at high nozzle pressure ratios. Boattail injection is more effective if used in regions of separated flow. (Author).

Download or read book Effects of Fineness and Closure Ratios on Boattail Drag of Circular arc Afterbody Models with Jet Exhaust at Mach Numbers Up to 1 3 written by David E. Reubush and published by . This book was released on 1973 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of variations in fineness ratio and closure ratio on the boattail drag of circular-arc afterbody models were investigated at static conditions and at Mach numbers from 0.40 to 1.30. Jet total-pressure ratio was varied from jet off to about 6, depending on Mach number. Reynolds number based on model maximum diameter varied from about 1.2 million to 2.18 million. Angle of attack was varied from -4 deg to 8 deg. The results indicate that, at subsonic speeds before the drag rise and at a scheduled pressure ratio, the total drag (pressure plus calculated skin friction) is approximately equal for configurations with the same closure ratio. Also, for configurations with the same closure ratio, increasing fineness ratio results in an increased drag-rise Mach number; and for configurations with the same fineness ratio, increasing closure ratio results in an increased drag-rise Mach number.