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Lift Drag And Static Longitudinal Stability Data From An Exploratory Investigation At A Mach Number Of 686 Of An Airplane Configuration Having A Wing Of Trapezoidal Plan Form
Download Lift Drag And Static Longitudinal Stability Data From An Exploratory Investigation At A Mach Number Of 686 Of An Airplane Configuration Having A Wing Of Trapezoidal Plan Form full books in PDF, epub, and Kindle. Read online Lift Drag And Static Longitudinal Stability Data From An Exploratory Investigation At A Mach Number Of 686 Of An Airplane Configuration Having A Wing Of Trapezoidal Plan Form ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
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 Static Longitudinal, Directional, and Lateral Stability and Control Data at a Mach Number of 6.83 of the Final Configuration of the X-15 Research Airplane by : Jim A. Penland
Download or read book Static Longitudinal, Directional, and Lateral Stability and Control Data at a Mach Number of 6.83 of the Final Configuration of the X-15 Research Airplane written by Jim A. Penland and published by . This book was released on 1960 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence by : John A. Axelson
Download or read book An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence written by John A. Axelson and published by . This book was released on 1948 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability.
Book Synopsis Experimental Stability and Control Results at Mach 19 of an Entry Vehicle Designed for an Intermediate Lift-drag Ratio by : Patrick J. Johnston
Download or read book Experimental Stability and Control Results at Mach 19 of an Entry Vehicle Designed for an Intermediate Lift-drag Ratio written by Patrick J. Johnston and published by . This book was released on 1968 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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 Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical-tail-load Characteristics of a Complete Model Having a Delta Wing by : Edward C. Polhamus
Download or read book Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical-tail-load Characteristics of a Complete Model Having a Delta Wing written by Edward C. Polhamus and published by . This book was released on 1958 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation at high subsonic speeds has been conducted to determine the effect of fuselage forebody strakes on the static stability and the vertical-tail-load characteristics of an airplane-type configuration having a delta wing. The tests were made at Mach numbers from 0.60 to 0.92 corresponding to Reynolds numbers from 3,000,000 to 4,200,000, based on the wing mean aerodynamic chord, and at angles of attack from approximately -2 to 24 degrees.
Book Synopsis An Investigation at Mach Numbers 1.94 and 2.41 of Jet Effects Upon the Longitudinal and Directional Stability of a General Aircraft Configuration Employing Wing-tip-mounted Nacelles by : Frank L. Clark
Download or read book An Investigation at Mach Numbers 1.94 and 2.41 of Jet Effects Upon the Longitudinal and Directional Stability of a General Aircraft Configuration Employing Wing-tip-mounted Nacelles written by Frank L. Clark and published by . This book was released on 1958 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Longitudinal Stability Characteristics at Transonic Speeds of a Rocket-propelled Model of an Airplane Having a 45 Degree Swept Wing of Aspect Ratio 6.0 by : John C. McFall
Download or read book Longitudinal Stability Characteristics at Transonic Speeds of a Rocket-propelled Model of an Airplane Having a 45 Degree Swept Wing of Aspect Ratio 6.0 written by John C. McFall and published by . This book was released on 1954 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic characteristics at Mach 6 of a hypersonic research airplane concept having a 70 ̊swept delta wing by : Louis E. Clark
Download or read book Aerodynamic characteristics at Mach 6 of a hypersonic research airplane concept having a 70 ̊swept delta wing written by Louis E. Clark and published by . This book was released on 1977 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Influence of Large Amounts of Wing Sweep on Stability and Control Problems of Aircraft by : Hartley Akin Soule
Download or read book Influence of Large Amounts of Wing Sweep on Stability and Control Problems of Aircraft written by Hartley Akin Soule and published by . This book was released on 1946 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: The use of large amounts of sweep has been suggested in this country and in Germany as a means of avoiding some of the drag increase and stability and control difficulties encountered in high-speed flight with conventional straight-wing airplanes. Experience with sweep in tailless airplanes and studies made since this suggested has been made have indicated that the use of a large amount of sweep will, in itself, introduce stability and control problems of sufficient magnitude and complexity to require considerable research, particularly for flight at high angles of attack. The paper discusses these problems and, although no proved solutions are given, in some cases promising lines for further investigation are presented.
Book Synopsis A Parametric Study of Planform and Aeroelastic Effects on Aerodynamic Center, [alpha]- and Q-stability Derivatives by : Jan Roskam
Download or read book A Parametric Study of Planform and Aeroelastic Effects on Aerodynamic Center, [alpha]- and Q-stability Derivatives written by Jan Roskam and published by . This book was released on 1973 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Lee-surface Volume Addition on Longitudinal Aerodynamics of a High-lift-drag-ratio Wing-body Configuration at Mach 6.0 by : David R. Stone
Download or read book Effects of Lee-surface Volume Addition on Longitudinal Aerodynamics of a High-lift-drag-ratio Wing-body Configuration at Mach 6.0 written by David R. Stone and published by . This book was released on 1968 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Stability and Control Characteristics of an Airplane Model with Tail Surfaces Outboard of the Wing Tips at a Mach Number of 2.01 by : Cornelius Driver
Download or read book Static Stability and Control Characteristics of an Airplane Model with Tail Surfaces Outboard of the Wing Tips at a Mach Number of 2.01 written by Cornelius Driver and published by . This book was released on 1959 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free-flight Measurements of the Zero-lift Drag of Several Wings at Mach Numbers from 1.4 to 3.8 by : H. Herbert Jackson
Download or read book Free-flight Measurements of the Zero-lift Drag of Several Wings at Mach Numbers from 1.4 to 3.8 written by H. Herbert Jackson and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of a Tailless Fixed-wing Supersonic Transport Configuration at Mach Number 2.20 by : Gerald V. Foster
Download or read book Aerodynamic Characteristics of a Tailless Fixed-wing Supersonic Transport Configuration at Mach Number 2.20 written by Gerald V. Foster and published by . This book was released on 1964 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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