Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 44
Book Description
Longitudinal and Lateral Aerodynamic Characteristics at Mach Numbers of 3.00, 3.96, and 4.65 of a Low-fineness-ratio Elliptical Hypersonic Configuration Having Variable-sweep Wing Panels
Author: The Transonic Longitudinal and Lateral Aerodynamic Characteristics of a Low-fineness-ratio Elliptic Hypersonic Configuration Employing Variable Sweep Wing Panels for Improving Subsonic Lift and Performance
Author: Longitudinal Aerodynamic Characteristics at Mach Numbers from 0.40 to 1.10 of a Blunted Right-trangular Pyramidal Lifting Reentry Configuration Employing Variable-sweep Wing Panels
Author: Bernard SpencerPublisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 80
Book Description
Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.20 of a V/STOL Airplane Configuration with a Variable-sweep Wing and with a Skewed Wing Design
Author: Odell A. MorrisPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Book Description
Longitudinal and Lateral Aerodynamic Characteristics at Mach Numbers from 0.60 to 4.63 for Two Variable-sweep Configurations
Author: Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.20 of a Variable-wing-sweep STOL Configuration
Author: Gerald V. FosterPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 32
Book Description
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
Author: Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
Book Description
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.
Longitudinal Aerodynamic Characteristics at Mach Numbers from 0.50 to 1.19 of a Supersonic Transport Model with a Modified M Wing
Author: Edward J. RayLongitudinal Aerodynamic Characteristics at Mach Numbers from 0.28 to 2.50 of a Multipurpose Tactical Airplane Configuration Having Variable-sweep Wings and Externally Mounted Engines
Author: Aerodynamic Characteristics at Mach Numbers of 1.5, 1.8, and 2.0 of a Blended Wing-body Configuration with and Without Integral Canards
Author: A. Warner RobinsPublisher:
ISBN:
Category : Hypersonic planes
Languages : en
Pages : 68
Book Description