Download or read book Jet Effects on the Drag of Conical Afterbodies at Supersonic Speeds written by William B. Compton and published by . This book was released on 1972 with total page 49 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 Jet Effects at Supersonic Speeds on Base and Afterbody Pressures of a Missile Model Having Single and Multiple Jets written by Nickolai Charczenko and published by . This book was released on 1963 with total page 46 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 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 NASA Technical Note written by and published by . This book was released on 1972 with total page 536 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 Aerodynamics of Airframe engine Integration of Supersonic Aircraft written by Mark R. Nichols and published by . This book was released on 1966 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Method for Estimating Jet Interference on Afterbody Drag at Supersonic Speeds written by British Aircraft Corporation and published by . This book was released on 1962 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Handbook of Supersonic Aerodynamics written by Johns Hopkins University. Applied Physics Laboratory and published by . This book was released on 1961 with total page 372 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Aerothermodynamics of Aircraft Gas Turbine Engines written by and published by . This book was released on 1978 with total page 770 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 A Free flight Investigation of the Effects of Simulated Sonic Turbojet Exhaust on the Drag of a Boattail Body with Various Jet Sizes from Mach Number 0 87 to 1 50 written by Ralph A. Falanga and published by . This book was released on 1955 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three 7.5 degree boattail bodies of revolution with varying base-annulus areas and jet sizes provided with simulated-turbojet-exhaust rocket motors were flight-tested to determine the jet interference effects on drag over a Mach number range from approximately 0.87 to 1.5. The results indicated that in the transonic and low-supersonic speed range the jet caused positive pressure increments on the base and boattail which appreciably reduced the configuration drag from the power-off condition. At the high supersonic speeds, the jet caused positive pressure increments only on the base and resulted in a smaller reduction in body drag from power-off conditions.

Download or read book Jet Effects on Cylindrical Afterbodies Housing Sonic and Supersonic Nozzles which Exhaust Against a Supersonic Stream at Angles of Attack from 90 to 180 written by Lovick O. Hayman and published by . This book was released on 1962 with total page 54 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 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 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.