Download or read book Aerodynamic Characteristics of Low Aspect Ratio Fins at Mach Numbers from 0 80 to 1 30 written by D.K. Smith and published by . This book was released on 1971 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of Several Low Aspect Ratio Stabilizer Fins at Mach Numbers from 0 8 to 1 3 written by J. M. Whoric and published by . This book was released on 1972 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of Low Aspect Ratio Fins at Mach Numbers from 0 80 to 1 30 written by D.K. Smith and published by . This book was released on 1971 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1960 with total page 450 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on 1964 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Aerodynamic Characteristics of Wrap around Fins at Mach Numbers of 0 3 to 3 0 written by C. Wayne Dahlke and published by . This book was released on 1976 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of investigations into many of the geometric and flow parameters influencing the aerodynamics of wrap-around fins are presented in this report. Particular emphasis is placed on defining static and dynamic roll characteristics between Mach numbers of 0.3 to 3.0. Among the geometric parameters highlighted are fin span, aspect ratio, leading edge sweep, leading edge shape, fin opening angle, and afterbody geometry. Comparisons of static stability, dynamic stability, and drag are made between the flat and the wrap- around fin. Problems associated with measurement of wrap-around fin rolling mounts are also discussed. An overview of the wrap-around fin roll moment characteristics are presented as an aid for making estimates and establishing testing techniques. This report supercedes RD-73-17.
Download or read book Monthly Catalog of United States Government Publications written by United States. Superintendent of Documents and published by . This book was released on 1963 with total page 1304 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 1978 with total page 1008 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 Data Bases and Data Base Systems Related to NASA s Aerospace Program written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch and published by . This book was released on 1981 with total page 516 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 AIAA 83 0410 AIAA 83 0501 written by and published by . This book was released on 1983 with total page 614 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 A Summary of Aerodynamic Characteristics for Wrap around Fins from Mach 0 3 to 3 0 written by James A. Humphrey and published by . This book was released on 1977 with total page 234 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wrap-around fin effectiveness for tube-launched missiles was investigated in a series of 6 wind tunnel tests. Wind tunnels were AEDC Propulsion Wind Tunnel, NASA/Langley Research Center Unitary Plan Wind Tunnel and McDonnell Douglas 4-foot Trisonic Wind Tunnel. Mach number range was 0.3 to 3.0. Basic model was a 2-caliber secant ogive nose with an 8-caliber cylindrical afterbody and 21 fin configurations. Variations in the coefficients are presented for changes in fin geometry including taper ratio and leading edge sweep angle, aspect ratio, exposed semi-span, and root chord length; opening angle, fully closed to 10 deg past fully open; and body step down.
Download or read book Data Bases and Data Base Systems Related to NASA s Aerospace Program A Bibliography with Indexes written by and published by . This book was released on 1981 with total page 516 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a Spoiler slot deflector Control on a 45 Sweptback Wing at Mach Numbers of 1 61 and 2 01 written by Douglas R. Lord and published by . This book was released on 1957 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of a spoiler-slot-deflector control on a 45 degree sweptback wing having an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. The model was equipped with a 15-percent-chord spoiler-slot-deflector extending from 13 o 78 percent of the wing semispan. The spoiler and deflector were hinged along the 60- and 75-percent-chord lines, respectively. Tests were made at a Reynolds number of 3,000,000 (based on the mean aerodynamic chord of the wing) and covered ranges of angles of attack from -3 to 15 degrees, spoiler projections from 0 to 8.0 percent chord, and deflector projections from 0 to 7.6 percent chord.
Download or read book The Aerodynamic Characteristics of Wrap Around Fins Including Fold Angle at Mach Numbers from 0 5 to 1 3 written by C. W. Dahlke and published by . This book was released on 1974 with total page 517 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the transonic wind tunnel to study the aerodynamic characteristics of wrap-around fins. Wrap-around fins with leading edge sweep angle on straight and step down bodies were tested. One unswept fin was tested simulating various opening angles from 10 degrees beyond fully open to a folding angle of 112.5 degrees. Force and moment data were obtained at Mach numbers from 0.5 to 1.3 at angles of attack up to 14 degrees and roll angles from 0 to 67.5 degrees. The results of the test are presented in plotted form for the main balance and all four fin balances.
