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  • AERODYNAMICS
  • Animals
  • 2015-2019
  • 1950-1954  (4)
  • 1951  (3)
  • 1950  (1)
  • 1
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    Method for estimating lift interference of wing-body combinations at supersonic speeds (1951)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Estimating method for lift interference of wing- body combinations at supersonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-A51J04
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Theoretical Investigation of Submerged Inlets at Low Speeds (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The general characteristics of the flow field in a submerged air inlet are investigated by theoretical, wind-tunnel, and visual-flow studies. Equations are developed for calculating the laminar and turbulent boundary-layer growth along the ramp floor for parallel, divergent, and convergent ramp walls, and a general equation is derived relating the boundary-layer pressure losses to the boundary-layer thickness. It is demonstrated that the growth of the boundary layer on the floor of the divergent-ramp inlet is retarded and that a vortex pair is generated in such an inlet. Functional relationships are established between the pressure losses in the vortices and the geometry of the inlet. A general discussion of the boundary layer and vortex formations is included, in which variations of the various losses and of the incremental external drag with mass-flow ratio are considered. Effects of compressibility are also discussed.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2323
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The spanwise distribution of lift for minimum induced drag of wings having a given lift and a given bending moment (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. The theory is limited to lifting surfaces traveling at subsonic speeds. It is found that the required shape of the downwash distribution can be obtained in an elementary way which is applicable to a variety of such problems. Expressions for the minimum drag and the corresponding spanwise load distributions are also given for the case in which the lift and the bending moment about the wing root are fixed while the span is allowed to vary. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span as compared with results for an elliptically loaded wing having the same total lift and bending moment.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2249 , Collected Works of Robert T. Jones; p 539-556
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Blockage Corrections for Three-Dimensional-Flow Closed-Throat Wind Tunnels, with Consideration of the Effect of Compressibility (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Theoretical blockage corrections are presented for a body of revolution and for a three-dimensional, unswept wing in a circular or rectangular wind tunnel. The theory takes account of the effects of the wake and of the compressibility of the fluid, and is based on the assumption that the dimensions of the model are small in comparison with those of the tunnel throat. Formulas are given for correcting a number of the quantities, such as dynamic pressure and Mach number, measured in wind tunnel tests. The report presents a summary and unification of the existing literature on the subject
    Keywords: AERODYNAMICS
    Type: NACA-TR-995
    Format: application/pdf
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