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  • 1970-1974  (2)
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  • 1
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    Unknown
    A quasi-vortex-lattice method in thin wing theory (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A quasi-continuous method is developed for solving thin-wing problems. For the purpose of satisfying the wing boundary conditions, the spanwise vortex distribution is assumed to be stepwise-constant, while the chordwise vortex integral is reduced to a finite sum through a modified trapezoidal rule and the theory of Chebyshev polynomials. Wing-edge and Cauchy singularities are acounted for. The total aerodynamic characteristics are obtained by an appropriate quadrature integration. The two-dimensional results for airfoils without flap deflection reproduce the exact solutions in lift and pitching moment coefficients, the leading edge suction, and the pressure difference at a finite number of points. For a flapped airfoil, the present results are more accurate than those given by the vortex-lattice method. The three-dimensional results also show an improvement over the results of the vortex-lattice method. Extension to nonplanar applications is discussed.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 11; Sept
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Some characteristics of airfoil-jet interaction with Mach number nonuniformity (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The image method is used to examine the upper-surface-blowing jet-airfoil interaction with Mach number nonuniformity. The formulation represents an extension of the classical incompressible results (Ting and Liu, 1969; Koning, 1963). Some characteristics of the interaction are discussed. The main assumptions are (1) inviscid linear theory, (2) two-dimensional jet, (3) no turbulent mixing, and (4) no airfoil thickness effect. A plane jet with Mach number M sub 2 is assumed to be imbedded in a freestream of Mach number M sub 1. A thin airfoil is placed at a distance h below the lower jet surface. For h = 0, this may represent an idealized configuration with an upper-surface blowing jet.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 11; Aug. 197
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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