Download or read book Numerical Investigation of Engine Thrust and Forebody Strake Effects on Rocket Aerodynamic Characteristics at High Angle of Attack written by William von Klemperer Logan and published by . This book was released on 2006 with total page 192 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 1979 with total page 1096 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0 7 to 1 4 written by Calvin Wayne Dahlke and published by . This book was released on 1977 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a wind tunnel test, simulating rocket motor exhaust jet effects on missile aerodynamic at Mach numbers of 0.7 to 1.4 are presented. A normal jet plume simulator was used to induce afterbody boundary layer separation. Flow visualization techniques including both shadowgraph and oil flow photographs were taken. The primary emphasis for this report is the force and moment measurements taken on twelve configurations including: five tail fin configurations; body alone; three forward fin configurations; body flare combination; and two combinations of forward fins/strakes with tail fins. All force and moment coefficients are presented in plotted form. One configuration is shown with ground plane interference simulation. (Author).
Download or read book An Experimental Investigation Using a Normal Jet Plume Simulator to Determine Jet Plume Effects on a Long Slender Rocket Configuration at Mach Numbers from 0 2 to 1 5 written by James H Henderson and published by . This book was released on 1977 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental aerodynamic investigations were conducted at the AEDC 16-foot Transonic Wind Tunnel to determine longitudinal stability characteristics of a long slender rocket configuration with simulated jet plume. The effect of jet plume on rocket aerodynamics is given over an angle of attack range from -11 to 11 degrees at Mach numbers from 0.2 to 1.5. Plume simulator chamber pressure varied from 0 to 600 psia. Individual cruciform fin aerodynamic loads are also shown over the same ranges. (Author).
Download or read book Effects of Body and Fin Deflections on the Aerodynamic Characteristics in Pitch of a 0 065 scale Model of a Four stage Rocket Configuration at Mach Numbers of 1 41 and 1 82 written by Ross B. Robinson and published by . This book was released on 1959 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1994 with total page 1036 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Rocket model Investigation of Lateral Stability Characteristics and Power Effects of a Jet engine Airplane Configuration with Tail Boom at Mach Numbers from 1 15 to 1 37 written by T. Bradley Curry and published by . This book was released on 1961 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Simulated Retrorockets on the Aerodynamic Characteristics of a Body of Revolution at Mach Numbers from 0 25 to 1 90 written by Victor L. Peterson and published by . This book was released on 1962 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics in Pitch of a 1 7 scale Model of a Two and Three stage Rocket Configuration at Mach Numbers of 0 4 to 4 63 written by William F. Hinson and published by . This book was released on 1969 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic characteristics in pitch of scale model of two and three stage rocket configuration at Mach numbers of 0.4 to 4.63.
Download or read book Static Aerodynamic Characteristics of Three Rocket vehicle Configurations at Mach Numbers from 1 80 to 4 63 Including Some Effects of Fin Size Fin Cant and Auxiliary Rocket Motors written by Dennis E. Fuller and published by . This book was released on 1963 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of an Upper Stage Rocket Plane with External burning Thrust Augmentation written by E. E. Callens and published by . This book was released on 1973 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: Some fundamental aspects of a regeneratively cooled, upper stage rocket plane with external-burning thrust augmentation are investigated analytically. Cases considered are only the ejected coolant is burned externally and all of the thrust required for sustained cruise is provided by external burning. One conclusion is that external-burning configurations offer an apparent advantage over internal propulsion systems in that the total vehicle cooling requirement for high-speed operation is much less for the external- burning regeneratively cooled configuration. Also, the fuel required for propulsion by an external-burning configuration greatly exceeds the fuel required for cooling.
Download or read book Aerodynamic Control of Slender Bodies at High Angles of Attack written by Vijaya Sirangu and published by . This book was released on 2010 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental and numerical investigations have been conducted on the aerodynamic control and maneuvering of slender bodies at high angles of attack. The study was conducted on an U.S. NAVY countermeasure concept projectile termed GuiDED Missile, and rectangular aftbody strakes were used to control the flow at high angles of attack. Forebody geometries studied include O-give, hemisphere and elliptical geometries. The optimal forebody design was based on maximum strake-induced mean yawing moment obtainable, minimum natural flow asymmetry, and minimum forebody-induced flow oscillation. The results show that the most effective flow control at high angles of attack is achieved with the O-give nose forebody geometry. For the O-give nose geometry, impacts of various body components including fairings, forebody wings and aftbody fins on the overall control performance were investigated. Effects of strake height, length, axial and azimuthal locations were studied, and an optimal rectangular strake planform was determined. Off-surface flow visualizations were conducted to study the flow fields associated with O-give, hemisphere and elliptical forebody geometries, and the optimal strake in combination with O-give forebody. Numerical simulations using FLUENT were conducted at low angles of attack for the baseline model with O-give and hemispheric forebodies. Simulations were performed at different Mach numbers for the O-give nose. The results obtained from the simulations were compared to that of the experiments.
Download or read book Experimental Study of Effects of Geometric Variables on Performance of Conical Rocket Engine Exhaust Nozzles written by Harry E. Bloomer and published by . This book was released on 1961 with total page 66 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 Aerodynamic Characteristics in Pitch of Several Triple body Missile Configurations at Mach Numbers 0 6 to 1 4 written by Earl D. Knechtel and published by . This book was released on 1956 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the longitudinal aerodynamic characteristics at transonic speeds of missile configurations having three blunted cone-cylinder bodies. Modifications of the basic model were tested to indicate the effects of (a) relative lengths of coplanar bodies, (b) seals between the cylindrical portions of the bodies, (c) horizontal connecting surfaces near the rear of the bodies, and (d) triangular rather than coplanar body grouping. Lift, drag, and pitching-moment data were obtained at angles of attack from -4 to 12 degrees and Mach numbers from 0.6 to 1.4 for a constant Reynolds number of 5,500,000, based on average body length.
Download or read book Experimental Investigation of Base Heating and Rocket Hinge Moments for a Simulated Missile Through a Mach Number Range of 0 8 to 2 0 written by Bruce G. Chiccine and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Static Aerodynamic Characteristics of a Two stage and a Three stage Rocket Vehicle at Mach Numbers from 1 47 to 4 63 written by Clarence A. Brown and published by . This book was released on 1962 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
