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Experimental Investigation At A Mach Number Of 311 Of The Lift Drag And Pitching Moment Characteristics Of Five Blunt Lifting Bodies
Download Experimental Investigation At A Mach Number Of 311 Of The Lift Drag And Pitching Moment Characteristics Of Five Blunt Lifting Bodies full books in PDF, epub, and Kindle. Read online Experimental Investigation At A Mach Number Of 311 Of The Lift Drag And Pitching Moment Characteristics Of Five Blunt Lifting Bodies ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Experimental Investigation at a Mach Number of 3.11 of the Lift, Drag, and Pitching-moment Characteristics of Five Blunt Lifting Bodies by : William Letko
Download or read book Experimental Investigation at a Mach Number of 3.11 of the Lift, Drag, and Pitching-moment Characteristics of Five Blunt Lifting Bodies written by William Letko and published by . This book was released on 1960 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Lift and Drag Characteristics at Subsonic Speeds and at a Mach Number of 1.9 of a Lifting Circular Cylinder with a Fineness Ratio of 10 by : Vernard E. Lockwood
Download or read book Lift and Drag Characteristics at Subsonic Speeds and at a Mach Number of 1.9 of a Lifting Circular Cylinder with a Fineness Ratio of 10 written by Vernard E. Lockwood and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis THE LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A RE-ENTRY CONFIGURATION BASED ON A BLUNT 13 DEG HALF-CONE AT MACH NUMBERS TO 0.92 by :
Download or read book THE LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A RE-ENTRY CONFIGURATION BASED ON A BLUNT 13 DEG HALF-CONE AT MACH NUMBERS TO 0.92 written by and published by . This book was released on 1961 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 by : L. J. Obery
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 written by L. J. Obery and published by . This book was released on 1951 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation to determine the external and internal flow characteristics of a typical ram-jet-inlet configuration of an external-compression type utilizing an isentropic spike and a subsonic diffuser was conducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel. The model was investigated of a range of mass-flow ratios at angles of attack up to 10 degrees, free-stream Mach numbers of 1.59, 1.79, and 1.99, and a Reynolds number of approximately 2,400,000 based on inlet diameter.
Book Synopsis Experimental Heat-transfer Distributions on a Blunt Lifting Body at Mach 3.71 by : Robert L. Stallings
Download or read book Experimental Heat-transfer Distributions on a Blunt Lifting Body at Mach 3.71 written by Robert L. Stallings and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: The composite body consisted of a spherical nose segment, a delta-slab upper surface with blunt leading edges, wedge sides, and a conical lower surface. The tests were conducted both with and without roughness on the model for a range of angle of attack up to 400. Included is a complete tabulation of the experimental heatii rates and a discussion of the more significant findings.
Book Synopsis A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 by : Robert S. Osborne
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 written by Robert S. Osborne and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Effects of Support Interference on the Drag of Bodies of Revolution at a Mach Number of 1.5 by : Edward W. Perkins
Download or read book Experimental Investigation of the Effects of Support Interference on the Drag of Bodies of Revolution at a Mach Number of 1.5 written by Edward W. Perkins and published by . This book was released on 1951 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains the results of an experimental investigation to determine the effects of support interference on the base drag and fore drage of two bodies of revolution. The results show that the rear supports affect the drag of a body of revolution through the immediate influence on the pressures acting over the rear portions of the body and thus the magnitude of the interference depends on the afterbody shape of the model, the Reynolds number of flow, and the condition of the boundary layer.
Book Synopsis 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 by :
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.
Book Synopsis Static Aerodynamic Characteristics of a Scout Fin with an Enlarged Tip Control at Mach Numbers from 0.40 to 4.63 by : Robert J. Keynton
Download or read book Static Aerodynamic Characteristics of a Scout Fin with an Enlarged Tip Control at Mach Numbers from 0.40 to 4.63 written by Robert J. Keynton and published by . This book was released on 1971 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of an experimental investigation to determine the static longitudinal aerodynamic characteristics of a fin with an enlarged tip control and the hinge-moment coefficients of the enlarged tip control. The model was tested at angles of attack from -6 [degree] to 6 [degree] and fin tip control deflections from -20° to 20°. A 1/8-scale model of the Scout first stage, with a tangent ogive nose, was used for these tests. Basic data obtained include the pitching-moment, rolling-moment, and normal-force coefficients of the fin and the hinge-moment coefficient of the enlarged tip control.
Book Synopsis Flight Evaluation of HL-10 Lifting Body Handling Qualities at Mach Numbers from 0.30 to 1.86 by : Robert W. Kempel
Download or read book Flight Evaluation of HL-10 Lifting Body Handling Qualities at Mach Numbers from 0.30 to 1.86 written by Robert W. Kempel and published by . This book was released on 1974 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Investigation at Mach Numbers from 0.6 to 1.7 to Determine Drag and Base Pressures on a Blunt-trailing-edge Airfoil and Drag of Diamond and Circular-arc Airfoils at Zero Lift by : John D. Morrow
Download or read book Flight Investigation at Mach Numbers from 0.6 to 1.7 to Determine Drag and Base Pressures on a Blunt-trailing-edge Airfoil and Drag of Diamond and Circular-arc Airfoils at Zero Lift written by John D. Morrow and published by . This book was released on 1950 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models having rectangular 6-percent-thick wings are presented for a Mach number range of 0.6 to 1.7. Wings of aspect ratio 2.7 having diamond, circular-arc, and blunt-trailing edge airfoil sections were tested. Pressures were measured on the base of the blunt-trailing-edge airfoil which had a rectangular section with a 40-percent-chord beveled leading edge. Although the blunt-trailing-edge airfoil had high drag throughout the Mach number range investigated, because of high base suction pressures, it is believed that the data presented can be used in the design of more nearly optimum blunt-base airfoils. Of the airfoils tested the circular-arc section had lowest drag at high-subsonic speeds, and the diamond section had lowest drag at supersonic speeds.
Book Synopsis Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in Air by : William I. Scallion
Download or read book Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in Air written by William I. Scallion and published by . This book was released on 1999 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 0.0196-scale model of the HL-20 lifting body, one of several configurations proposed for future crewed spacecraft, was tested in the Langley 31-Inch Mach 10 Tunnel. The purpose of the tests was to determine the effectiveness of fin-mounted elevons, a lower surface flush-mounted body flap, and a flush-mounted yaw controller at hypersonic speeds. The nominal angle-of-attack range, representative of hypersonic entry, was 20 to 41 degrees, the sideslip angles were 0, 2, and -2 degrees, and the test Reynolds number was 1.06 x 10[factor 6] based on model reference length. The aerodynamic, longitudinal, and lateral control effectiveness along with surface oil flow visualizations are presented and discussed. The configuration was longitudinally and laterally stable at the nominal center of gravity. The primary longitudinal control, the fin-mounted elevons, could not trim the model to the desired entry angle of attack of 30 degrees. The lower surface body flaps were effective for roll control and the associated adverse yawing moment was eliminated by skewing the body flap hinge lines. A yaw controller, flush-mounted on the lower surface, was also effective, and the associated small rolling moment was favorable.
Book Synopsis Investigation of the Variation of Maximum Lift for a Pitching Airplane Model and Comparison with Flight Results by : Paul W. Harper
Download or read book Investigation of the Variation of Maximum Lift for a Pitching Airplane Model and Comparison with Flight Results written by Paul W. Harper and published by . This book was released on 1948 with total page 706 pages. Available in PDF, EPUB and Kindle. Book excerpt: Apparatus was developed which utilized a pitching airplane model to determine maximum wing loads as a function of the rate of change of angle of attack. In order to evaluate the pitching-model technique, the maximum lift coefficient was determined as a function of the rate of change of angle of attack over a Mach number range from approximately 0.2 to 0.6 in wind-tunnel tests of a 1/20-scale model of a conventional single-engine fighter airplane and was conpared with existing flight data of this airplane. The wind-tunnel and flight results were found to be in good agreement.
Book Synopsis Lift Generation on a Circular Cylinder by Tangential Blowing from Surface Slots by : Vernard E. Lockwood
Download or read book Lift Generation on a Circular Cylinder by Tangential Blowing from Surface Slots written by Vernard E. Lockwood and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Lift, Drag, and Static Longitudinal Stability Data from an Exploratory Investigation at a Mach Number of 6.86 of an Airplane Configuration Having a Wing of Trapezoidal Plan Form by : Jim A. Penland
Download or read book Lift, Drag, and Static Longitudinal Stability Data from an Exploratory Investigation at a Mach Number of 6.86 of an Airplane Configuration Having a Wing of Trapezoidal Plan Form written by Jim A. Penland and published by . This book was released on 1955 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Lift and Drag Characteristics of the HL-10 Lifting Body During Subsonic Gliding Flight by : Jon S. Pyle
Download or read book Lift and Drag Characteristics of the HL-10 Lifting Body During Subsonic Gliding Flight written by Jon S. Pyle and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research Memorandum by : United States. National Advisory Committee for Aeronautics
Download or read book Research Memorandum written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1951 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
