Aerodynamic Characteristics For A Booster Launched Folding Wing Entry Vehicle Suitable For Sustained Operation As A Supersonic Aircraft
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Author |
: |
Publisher |
: |
Total Pages |
: 88 |
Release |
: 1963 |
ISBN-10 |
: NASA:31769000462922 |
ISBN-13 |
: |
Rating |
: 4/5 (22 Downloads) |
Synopsis Aerodynamic Characteristics for a Booster Launched Folding Wing Entry Vehicle Suitable for Sustained Operation as a Supersonic Aircraft by :
Author |
: |
Publisher |
: |
Total Pages |
: 46 |
Release |
: 1964 |
ISBN-10 |
: NASA:31769000663735 |
ISBN-13 |
: |
Rating |
: 4/5 (35 Downloads) |
Synopsis Characteristics of a Variable-geometry Entry Vehicle at Mach Numbers from 10.5 to 21.1 in Helium Flow by :
Author |
: Ernald Baker Graves |
Publisher |
: |
Total Pages |
: 52 |
Release |
: 1971 |
ISBN-10 |
: NASA:31769001178790 |
ISBN-13 |
: |
Rating |
: 4/5 (90 Downloads) |
Synopsis Supersonic Aerodynamic Characteristics of a Rocket-vehicle Model with Low-aspect-ratio Wing and Tail Surfaces by : Ernald Baker Graves
Author |
: Alan B. Kehlet |
Publisher |
: |
Total Pages |
: 42 |
Release |
: 1954 |
ISBN-10 |
: UOM:39015095100825 |
ISBN-13 |
: |
Rating |
: 4/5 (25 Downloads) |
Synopsis Aerodynamic Characteristics at Transonic and Supersonic Speeds of a Rocket-propelled Airplane Configuration Having a Diamond-plan-form Wing Aspect Ration 3.08 and a Low, Swept Horizontal Tail by : Alan B. Kehlet
Author |
: Edward J. Ray |
Publisher |
: |
Total Pages |
: 84 |
Release |
: 1966 |
ISBN-10 |
: UIUC:30112106659847 |
ISBN-13 |
: |
Rating |
: 4/5 (47 Downloads) |
Synopsis Transonic Aerodynamic Characteristics of a Tailless Fixed-wing Supersonic Transport Model by : Edward J. Ray
Author |
: George M. Ware |
Publisher |
: |
Total Pages |
: 76 |
Release |
: 1994 |
ISBN-10 |
: NASA:31769000522790 |
ISBN-13 |
: |
Rating |
: 4/5 (90 Downloads) |
Synopsis Supersonic Aerodynamic Characteristics of a Circular Body Earth-to-orbit Vehicle by : George M. Ware
Author |
: |
Publisher |
: |
Total Pages |
: 102 |
Release |
: 1964 |
ISBN-10 |
: NASA:31769000663867 |
ISBN-13 |
: |
Rating |
: 4/5 (67 Downloads) |
Synopsis Supersonic Aerodynamic Characteristics of a Recoverable Booster with Variations in Wing Planform by :
Author |
: |
Publisher |
: |
Total Pages |
: 80 |
Release |
: 1960 |
ISBN-10 |
: NASA:31769000457039 |
ISBN-13 |
: |
Rating |
: 4/5 (39 Downloads) |
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 :
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.
Author |
: Lowell E. Hasel |
Publisher |
: |
Total Pages |
: 36 |
Release |
: 1952 |
ISBN-10 |
: UOM:39015086464818 |
ISBN-13 |
: |
Rating |
: 4/5 (18 Downloads) |
Synopsis Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-body Combinations Having Cambered Wings with an Aspect Ratio of 3.5 and a Taper Ratio of 0.2 by : Lowell E. Hasel
Author |
: Ross B. Robinson |
Publisher |
: |
Total Pages |
: 32 |
Release |
: 1952 |
ISBN-10 |
: UOM:39015086464974 |
ISBN-13 |
: |
Rating |
: 4/5 (74 Downloads) |
Synopsis Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-body Combinations Having Cambered Wings with an Aspect Ratio of 3.5 and a Taper Ratio of 0.2 by : Ross B. Robinson