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  • AERODYNAMICS  (8)
  • 1975-1979  (8)
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Keywords
Years
Year
  • 1
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    Sonic-boom wave-front shapes and curvatures associated with maneuvering flight (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Sonic-boom wave shapes and caustic lines generated by an airplane performing a general maneuver are studied. The equations are programmed for graphical output as a perspective view of the wave shape. This quasi three-dimensional presentation provides a qualitative insight into the effects of the maneuver on the wave shape and the caustic locations. For the special case of planar maneuvers, the principal curvatures of the wave front are derived. These curvatures are needed to calculate the sound field in the vicinity of a caustic. The results of the analysis are applicable not only to sonic-boom studies but also to the calculation of noise generated by a supersonic rotor or propeller blade tip.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1611 , L-13339
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Investigation of flow characteristics over missile bodies at supersonic speeds (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three missile body shapes tested at Mach numbers of 1.50, 2.16, and 2.86 with angles of attack up to 30 degrees are described. The flow characteristics for each body shape are examined. The measured aerodynamic forces and moments are presented. The use of flow visualization techniques are described and the results such as vortex effects are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1579 , L-13224
    Format: application/pdf
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  • 3
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    A distributed vortex method for computing the vortex field of a missile (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Vortex sheet development in the flow field of a missile was investigated by approximating the sheets in the cross-flow plane with short straight-line segments having distributed vorticity. In contrast with the method that represents the sheets as lines of discrete vortices, this distributed vortex method produced calculations with a high degree of computational stability.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1183 , L-11963
    Format: application/pdf
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  • 4
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    Adaptation of the Theodorsen theory to the representation of an airfoil as a combination of a lifting line and a thickness distribution (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The theory provides a direct method for resolving an airfoil into a lifting line and a thickness distribution as well as a means of synthesizing thickness and lift components into a resultant airfoil and computing its aerodynamic characteristics. Specific applications of the technique are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8117 , L-10476
    Format: application/pdf
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  • 5
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    A nonlinear theory for airfoils with trailing-edge jet flap (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A nonlinear procedure for computing the pressure distribution on an airfoil with a trailing edge jet flap is described. The method is not restricted to thin airfoils or shallow jet-deflection angles. Correlation with experiment indicates that the characteristics of the pressure distribution are predicted by the theory, but the effect of entrainment is overpredicted with the entrainment coefficient used.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8368 , L-11126
    Format: application/pdf
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  • 6
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    Estimation of attainable leading-edge thrust for wings at subsonic and supersonic speeds (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The factors which place limits on the theoretical leading edge thrust are identified. An empirical method for the estimation of attainable thrust is presented. The method is based on the use of simple sweep theory to permit a two dimensional analysis, the use of theoretical airfoil programs to define thrust dependence on local geometric characteristics, and the examination of experimental two dimensional airfoil data to define limitations imposed by local Mach numbers and Reynolds numbers. Comparisons of theoretical and experimental aerodynamic characteristics for a series of wing body configurations are examined.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1500 , L-13032
    Format: application/pdf
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  • 7
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    Slender body treatment of some specialized problems associated with elliptic-cross-section missile configurations (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Slender body methods were applied to some specialized problems associated with missile configurations with elliptic cross sections. Expressions are derived for computing the velocity distribution on the nose section when the ellipse eccentricity is varying longitudinally on the missile. The cross flow velocity on a triform fin section is also studied.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8495 , L-11425
    Format: application/pdf
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  • 8
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    A theoretical investigation of forebody shapes designed for natural laminar boundary-layer flow (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design of forebody shapes for natural laminar flow is discussed. For subsonic flow, computed results for three shapes of different fineness ratios indicate that laminar flow can be attained under conditions that approximate those on the forebody of a cruise missile flying at a low altitude at a high subsonic Mach number. For supersonic (Mach 2.00) design, a one-parameter family of hyperbolic arcs was used to generate forebody shapes having a favorable pressure gradient over the forebody length. Computed results for these shapes indicated laminar and transitional flow over the range of Reynolds numbers considered.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1375 , L-12550
    Format: application/pdf
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