Download or read book Wind Tunnel Investigation If a Missile with an Operational Mid body Turbojet Engine written by Lamar M. Auman and published by . This book was released on 1993 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Mach Numbers from 1 90 to 2 86 of a Canard controlled Missile with Ram air jet Spoiler Roll Control written by A. B. Blair and published by . This book was released on 1978 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Altitude Wind Tunnel Investigation of the Prototype J40 WE 8 Turbojet Engine Without Afterburner written by John E. McAulay and published by . This book was released on 1953 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind tunnel Investigation of Nozzle Hinge Moments for a Large Ballistic Missile Having Two Gimbaled Rocket Motors written by and published by . This book was released on 1959 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Tests of a Full scale Air launched Cruise Missile with an Installed Turbofan Engine written by H. E. McDill and published by . This book was released on 1977 with total page 206 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Technique for Firing Dynamically Scaled Missile Models in Wind Tunnels and for Measuring Rocket motor Sound and Pressure Fluctuations written by William J. Alford and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Altitude Wind Tunnel Investigation of the Performance of Compressor Combustor and Turbine Components of Prototype J47D RX1 1 Turbojet Engine written by John M. Farley and published by . This book was released on 1960 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Supersonic Speeds of a Canard controlled Missile with Fixed and Free rolling Tail Fins written by A. B. Blair and published by . This book was released on 1978 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The High speed Flexible throat Supersonic Wind Tunnel written by and published by . This book was released on 1948 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Results of Transonic Wind Tunnel Investigation to Determine the Effects of Nozzle Geomatry and Jet Plume on the Aerodynamics of a Body of Revolution Technical Report written by James H. Henderson and published by . This book was released on 1972 with total page 235 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Wind tunnel Investigation of a Ram air spoiler Roll control Device on a Forward control Missile at Supersonic Speeds written by A. B. Blair (Jr) and published by . This book was released on 1978 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Results of a Transonic Wind Tunnel Investigation of Trust Effects on the Aerodynamics of the Longbow Missile Configuration written by J. H. Henderson and published by . This book was released on 1973 with total page 81 pages. Available in PDF, EPUB and Kindle. Book excerpt: ERODYNAMICS OF THE Longbow Missile Configuration. Technical rept., Henderson, J. H. ;RD-TR-73-18DA-1-M-262303-A-214*Antiradiation missiles, *Transonic characteristics, *Wind tunnel tests, *Thrust, Wind tunnel models, Bodies of revolution, Fins, Aerodynamic configurations, Air to surface missiles, Jets, Air, Angle of attack, Base pressure, Plumes*LONGBOW missilesTransonic wind tunnel tests were conducted on a strut-mounted model of the LONGBOW missile configuration to determine thrust effects on a body of revolution afterbody with fins located at various longitudinal positions. Thrust was simulated by a cold air axial jet. Base pressure and afterbody forces and moments were measured. The test was conducted at Mach numbers from 0.4 to 1.25 and at angles of attack from -2 degrees to 10 degrees. Jet thrust was varied from 0 to 400 pounds. Reynolds number per foot varied from 0.7 to 1.7 million. (Modified author abstract).
Download or read book Transonic Wind Tunnel Investigation of Thrust Effects on the Longitudinal Stability Characteristics of Several Body fin Configurations written by James H. Henderson and published by . This book was released on 1974 with total page 872 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic wind tunnel tests were conducted on a sting-mounted model to determine thrust effects on longitudinal stability characteristics of several body-fin combinations. The plume was simulated by cold air ejected from a series of sonic jets normal to the missile axis. One fin configuration was tested at several longitudinal positions. Adverse plume effects on stability were reduced by location of fins a distance forward of the base. The test was conducted at the Calspan Corporations' 8 foot Transonic Wind Tunnel at Mach numbers ranging from 0.4 to 1.25. Angles of attack ranged from -4 degrees to 12 degrees. Data were also obtained at roll angles of 22.5 degrees and 45 degrees for one configuration.
Download or read book Transonic Wind Tunnel Investigation of Thrust Effects on Missile Aerodynamics written by R. J. Dennis and published by . This book was released on 1973 with total page 278 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic wind tunnel tests were conducted on an Army Missile Command (AMC) base drag research missile model in the Calspan Corporation 8-Foot Transonic Wind Tunnel during January of 1973. These tests were conducted in order to determine the effect of jet plumes on the stability characteristics of fin and ringtail afterbody confugurations. Afterbody forces and moments and base pressure were measured at jet thrust levels from zero to 400 pounds. The tests were conducted at Mach numbers from zero to 1.25 and at angles of attack from -5 to +10 degrees. The report presents details of the test program, an outline of the test procedures, and results of the investigation in tabular form.
Download or read book Preliminary Low Speed Wind Tunnel Investigation of Some Aspects of the Aerodynamic Problems Associated with Missiles Carried Externally in Positions N written by U. S. Government Printing Office and published by BiblioGov. This book was released on 2013-07 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems associated with the use of air-to-air missiles when carried externally on aircraft. Measurements of the forces and moments on a missile model for a range of positions under the mid-semispan location of a 45deg sweptback wing indicated longitudinal and lateral forces with regard to both carriage and release of the missiles. Surveys of the characteristics of the flow field in the region likely to be traversed by the missiles showed abrupt gradients in both flow angularity and in local dynamic pressure. Through the use of aerodynamic data on the isolated missile and the measured flow-field characteristics, the longitudinal forces and moments acting on the missile while in the presence of the wing-fuselage combination could be estimated with fair accuracy. Although the lateral forces and moments predicted were qualitatively correct, there existed some large discrepancies in absolute magnitude.
Download or read book Wind tunnel Investigation at Supersonic Speeds of a Canard controlled Missile with Fixed and Free rolling Tail Fins written by and published by . This book was released on 1978 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of a Spinning Missile with Active Canard Control written by Lamar M. Auman and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
