Download or read book Supersonic Aerodynamic Characteristics of a Low Aspect Ratio Missile Model with Wing and Tail Controls and with Tails in Line and Interdigitated written by Ernald B. Graves and published by . This book was released on 1972 with total page 272 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book SUPERSONIC AERODYNAMIC CHARACTERISTICS OF A LOW ASPECT RATIO MISSLE MODEL WITH WING AND TAIL CONTROLS AND WITH TAILS IN LINE AND INTERDIGITATED written by UNITED STATES. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION. and published by . This book was released on 1966 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Aerodynamic Characteristics of a Cruciform Missile Configuration with Low a spect ratio Wings and In line Tail Controls written by and published by . This book was released on 1964 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Aerodynamic Characteristics of a Rocket vehicle Model with Low aspect ratio Wing and Tail Surfaces written by Ernald Baker Graves and published by . This book was released on 1971 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Aerodynamic Characteristics of a Sparrow III Type Missile Model with Wing Controls and Comparison with Existing Tail control Results written by William J. Monta and published by . This book was released on 1977 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Aerodynamic Characteristics of a Sparrow 3 Type Missile Model with Wing Controls and Comparison with Existing Tail control Results written by and published by . This book was released on 1977 with total page 88 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 1972 with total page 946 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 Supersonic Stability and Control Characteristics of a Cruciform Missile Model with Delta Wings and Aft Tail Fin Control written by and published by . This book was released on 1979 with total page 124 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 1979 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Stability and Control Characteristics of a Cruciform Missile Model with Delta Wings and Aft Tail Fin Controls written by William A. Corlett and published by . This book was released on 1979 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a Maneuverable Missile with Cruiform Wings and In line Canard Surfaces at Mach Numbers from 0 50 to 4 63 written by and published by . This book was released on 1966 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Aerodynamic Characteristics of a Low Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1 86 and a Body of Fineness Ratio 20 written by and published by . This book was released on 1960 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.
Download or read book Supersonic Aerodynamic Characteristics of a Low drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1 86 and a Body of Fineness Ratio 20 written by Warren Gillespie Jr. and published by . This book was released on 1960 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Configured Missile Development written by Robert J. Krieger and published by . This book was released on 1980 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of a program that investigated aerodynamic configuring as a method of improving long range supersonic cruise and maneuvering missile performance. Non-circular body, lifting body, blended wing body, wing-body and favorable interference concepts were developed and wind tunnel tested. Substantial improvements in cruise range were shown to result from aero configuring.
Download or read book The Aerodynamics of Some Guided Projectiles written by and published by . This book was released on 1984 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Aerodynamic Assessment of Various Missile Configuration Concepts written by and published by . This book was released on 1983 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Stability Technology for Maneuverable Missiles written by Gennaro F. Aiello and published by . This book was released on 1979 with total page 396 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study developed empirical methods to predict aerodynamic characteristics of body-tail, body-wing-tail and body-strake-tail missile configurations. Methods cover the Mach number range from 0.6 to 3.0. Methods cover the individual body and tail characteristics at angles of attack from 0 to 180 degrees. For winged bodies the methods encompass angles of attack up to about 30 degrees. All mutual interference effects are accounted for, allowing accurate prediction of force and moment coefficients. (Author).
