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  • Other Sources  (8)
  • AERODYNAMICS  (4)
  • AIRCRAFT STABILITY AND CONTROL  (4)
  • 65D07
  • 1980-1984  (8)
Collection
  • Other Sources  (8)
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Keywords
  • AERODYNAMICS  (4)
  • AIRCRAFT STABILITY AND CONTROL  (4)
  • 65D07
Years
Year
  • 1
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    Chordwise and compressibility corrections for arbitrary planform slender wings (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The Lomax and Sluder method for adapting slender-wing theory to delta or rectangular wings by making chordwise and compressibility corrections is extended to cover wings of any arbitrary planform in subsonic and supersonic flows. The numerical accuracy of the present work is better than that of the Lomax-Sluder results. Comparison of the results of this work with those of the vortex-lattice method and Kernel function method for a family of Gothic and arrowhead wings shows good agreement. A universal curve is proposed for the evaluation of the lift coefficient of a low aspect ratio wing of an arbitrary planform in subsonic flow. The location of the center of pressure can also be estimated.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Aug. 198
    Format: text
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  • 2
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    A vortex-lattice method for calculating longitudinal dynamic stability derivatives of oscillating delta wings (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 21, p. 3626, Accession no. A81-44570
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA Journal (ISSN 0001-1452); 22; 6-12
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  • 3
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    Dynamic load measurements with delta wings undergoing self-induced roll oscillations (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 19, p. 2982, Accession no. A82-39098
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Aircraft (ISSN 0021-8669); 21; 30-36
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  • 4
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    A vortex-lattice method for calculating longitudinal dynamic stability derivatives of oscillating delta wings (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A nonsteady vortex-lattice method is introduced for predicting the dynamic stability derivatives of a delta wing undergoing an oscillatory motion. The analysis is applied to several types of small oscillations in pitch. The angle of attack varied between + or - 1 deg, with the mean held at 0 deg when the flow was assumed to be attached and between + or - 1 deg and the mean held at 15 deg when both leading-edge separation and wake roll-up were included. The computed results for damping in pitch are compared with several other methods and with experiments, and are found to be consistent and in good agreement.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 81-1876 , Atmospheric Flight Mechanics Conference; Aug 19, 1981 - Aug 21, 1981; Albuquerque, NM
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  • 5
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    A vortex-lattice method for calculating lifting-surface interference (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The interference effect of closely coupled lifting surfaces was investigated. A nonsteady vortex-lattice method was applied to calculate the steady-state and nonsteady lift characteristics of configurations having interference effects. The configurations consist of low-aspect-ratio delta wings, at low and high angles of attack. Leading-edge separation and wake roll-up are simulated by a time-dependent wake-shedding procedure. For steady-state flow conditions, this numerical procedure saves a considerable amount of computer time, compared with iterative methods, and yields the same results. A better understanding of the interference effect can be gained by using the method to study the transient behavior. The nonsteady approach also offers the capability of calculating various nonsteady motions, as is demonstrated in the calculation of the longitudinal damping.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-1662 , Aircraft Systems and Technology Conference; Aug 11, 1981 - Aug 13, 1981; Dayton, OH
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  • 6
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    Wind-tunnel measurements of wing-canard interference and a comparison with various theories (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Wind-tunnel tests and analyses of the aerodynamics of wing-canard combinations for low speed applications are presented. Systematic tests are conducted in a 7 x 10 wind tunnel to explore various combinations of wing-canard vertical and horizontal positioning. The goals of the tests are (1) to investigate potential improved stalling characteristics over conventional tail-aft configurations, (2) to investigate the existence of a lift coefficient advantage, and (3) to determine induced drag levels. The measurements obtained are compared with calculations made using the Prandtl-Munk theory, and with a vortex-lattice panel code. Results indicate that the panel code gives excellent results for lift and induced drag at moderate lift coefficient, whereas Prandtl-Munk theory gives conservative results for induced drag. The application is a light transport aircraft used for short-haul operations.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 810575 , Business Aircraft Meeting and Exposition; Apr 07, 1981 - Apr 10, 1981; Wichita, KS
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  • 7
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    A vortex-lattice method for the calculation of the nonsteady separated flow over delta wings (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An analysis is made of the wake structure and the forces on a delta wing as it undergoes nonsteady motion, wherein the flow separates at the leading edge. Comparisons of these predictions with existing experimental and theoretical data for the nonsteady linear and nonlinear motions indicate good agreement. It was found that the time-dependent, wake-shedding numerical procedure applied here for the wake rollup and the lift force calculation resulted in considerable saving of computer time over methods using the iterative wake rollup procedure. Calculated results for various motions of the delta wing, including the plunging motion, are presented for both the separated and the attached flow cases.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1803 , Aircraft Systems Meeting; Aug 04, 1980 - Aug 06, 1980; Anaheim, CA
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  • 8
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    Dynamic load measurements with delta wings undergoing self-induced roll-oscillations (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The aerodynamic forces acting on a delta wing, mounted on a free-to-roll sting-balance apparatus, were measured. Two wing planforms having leading edge sweeps of 76 and 80 deg were tested, but only the wing with the 80 deg sweep would undergo periodic self-induced roll oscillation. The time dependent forces and roll angles for this wing were then recorded for various test conditions. In these tests a considerable drop in the average normal force of the free-to-roll wing was measured, relative to the normal force obtained in the static tests. Also, the helium-bubble flow visualization technique was used to gain some insight into the periodic motion of the separated leading edge vortices.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 82-1320 , Atmospheric Flight Mechanics Conference; Aug 09, 1982 - Aug 11, 1982; San Diego, CA
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