Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 46
Book Description
Supersonic Aerodynamic Characteristics of Triangular Plan-form Models at Angles of Attack to 90 Degrees
Author: Supersonic Aerodynamic Characteristics of Some Reentry Concepts for Angles of Attack to 90 Deg
Author: Supersonic Aerodynamic Characteristics of Trianglular Plan Form Models at Angles of Attack to 90
Author: Lyle E. WigginsThe Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms
Author: Max A. HeasletPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 726
Book Description
A method is developed, consistent with the assumptions of small perturbation theory, which provides a means of determining for a known load distribution, the downwash behind a wing in supersonic flow. THe analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading.
NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information DivisionPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 2300
Book Description
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1040
Book Description
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.
U.S. Government Research & Development Reports
Author: Transonic Aerodynamic Characteristics of a Tailless Fixed-wing Supersonic Transport Model
Author: Edward J. RayPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 84
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.
Supersonic Aerodynamic Characteristics of an Advanced F-16 Derivative Aircraft Configuration
Author: Mike C. FoxPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 130
Book Description