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  • Other Sources  (11)
  • NASA Technical Reports  (11)
  • Bibliography on Seismology
  • Aerodynamics  (11)
  • 1930-1934  (6)
  • 1920-1924
Collection
  • Other Sources  (11)
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  • NASA Technical Reports  (11)
  • Bibliography on Seismology
Keywords
Years
Year
  • 1
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    The Minimum Induced Drag of Aerofoils (1923)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report helps explain the phenomenon of flight. It contains some theorems concerning the arrangement of airplane wings which are of considerable practical interest. In particular, it shows the theoretical reasons for the decrease of drag which accompanies all increase in the aspect ratio or lateral extension of a wing. The efficiency of a given arrangement of wings may be calculated from the formulae derived in this paper.
    Keywords: Aerodynamics
    Type: NACA-TR-121
    Format: application/pdf
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  • 2
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    The Inertial Coefficients of an Airship in a Frictionless Fluid (1924)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report deals with the investigation of the apparent inertia of an airship hull. The exact solution of the aerodynamical problem has been studied for hulls of various shapes and special attention has been given to the case of an ellipsoidal hull. In order that the results for this last case may be readily adapted to other cases, they are expressed in terms of the area and perimeter of the largest cross section perpendicular to the direction motion by means of a formula involving a coefficient K which varies only slowly when the shape of the hull is changed, being 0.637 for a circular or elliptic disk, 0.5 for a sphere, and about 0.25 for a spheroid of fineness ratio 7. For rough purposes it is sufficient to employ the coefficients, originally found for ellipsoids, for hulls otherwise shaped. When more exact values of the inertia are needed, estimates may be based on a study of the way in which K varies with different characteristics and for such a study the new coefficient possesses some advantage over one which is defined with reference to the volume of fluid displaced. The case of rotation of an airship hull has been investigated also and a coefficient has been defined with the same advantages as the corresponding coefficient for rectilinear motion.
    Keywords: Aerodynamics
    Type: NACA-TR-164
    Format: application/pdf
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  • 3
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    Aerodynamic Investigation of a Cup Anemometer (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This thesis presents the results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemisphere cup under the following conditions: (1) single cup with no interference; (2) single cup with three-cup interference; (3) four cups. The coefficients found in this research vary with Reynolds Number and are high as compared with those of Eiffel. The effect of interference upon a single cup is to increase the drag and normal force coefficients. The curve resulting from the summation of the coefficients for four cups agrees with the static torque curve of a Robinson type cup anemometer. All tests were carried on in the University of Detroit atmospheric wind tunnel during May 1933.
    Keywords: Aerodynamics
    Type: NACA-TN-502
    Format: application/pdf
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  • 4
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    Remarks on the Pressure Distribution over the Surface of an Ellipsoid, Moving Translationally Through a Perfect Fluid (1924)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note, prepared for the National Advisory Committee for Aeronautics, contains a discussion of the pressure distribution over ellipsoids when in translatory motion through a perfect fluid. An easy and convenient way to determine the magnitude of the velocity and of the pressure at each point of the surface of an ellipsoid of rotation is described. The knowledge of such pressure distribution is of great practical value for the airship designer. The pressure distribution over the nose of an airship hull is known to be in such good agreement with the theoretical distribution as to permit basing the computation of the nose stiffening structure on the theoretical distribution of pressure.
    Keywords: Aerodynamics
    Type: NACA-TN-196
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  • 5
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    Flow and Force Equations for a Body Revolving in a Fluid (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Part I gives a general method for finding the steady-flow velocity relative to a body in plane curvilinear motion, whence the pressure is found by Bernoulli's energy principle. Integration of the pressure supplies basic formulas for the zonal forces and moments on the revolving body. Part II, applying this steady-flow method, finds the velocity and pressure at all points of the flow inside and outside an ellipsoid and some of its limiting forms, and graphs those quantities for the latter forms. Part III finds the pressure, and thence the zonal force and moment, on hulls in plane curvilinear flight. Part IV derives general equations for the resultant fluid forces and moments on trisymmetrical bodies moving through a perfect fluid, and in some cases compares the moment values with those found for bodies moving in air. Part V furnishes ready formulas for potential coefficients and inertia coefficients for an ellipsoid and its limiting forms. Thence are derived tables giving numerical values of those coefficients for a comprehensive range of shapes.
    Keywords: Aerodynamics
    Type: NACA-TR-323
    Format: application/pdf
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  • 6
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    The Aerodynamic Forces on Airship Hulls (1924)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the new method for making computations in connection with the study of rigid airship, which was used in the investigation of the navy's ZR-1 by the special subcommittee of the National Advisory Committee for Aeronautics appointed for this purpose. It presents the general theory of the air forces on airship hulls of the type mentioned, and an attempt has been made to develop the results from the very fundamentals of mechanics without reference to some of the modern highly developed conceptions, which may not yet be thoroughly known to readers uninitiated into modern aerodynamics, and which may, perhaps, for all time remain restricted to a small number of specialists.
    Keywords: Aerodynamics
    Type: NACA-TR-184
    Format: application/pdf
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  • 7
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    General Potential Theory of Arbitrary Wing Section (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives the exact treatment of the problem of determining the 2-dimensional potential flow around wing sections of any type. The treatment is based directly on the solution of this problem as advanced by Theodorsen in NACA-TR-411. The problem condenses into the compact form of an integral equation capable of yielding numerical solutions by a direct process.
    Keywords: Aerodynamics
    Type: NACA-TR-452
    Format: application/pdf
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  • 8
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    Velocity Distribution in the Boundary Layer of a Submerged Plate (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report deals with the measurement of the velocity distribution of the air in the velocity of a plate placed parallel to the air flow. The measurements took place in a small wind tunnel where the diameter of the entrance cone is 30 cm and the length of the free jet between the entrance and exit cones is about 2.5 m. The measurements were made in the free jet where the static pressure was constant, which was essential for the method of measurement used.
    Keywords: Aerodynamics
    Type: NACA-TM-585 , Abhandlungen aus dem Aerodynamischen Institut an der Technischen Hochshcule Aachen; No. 8; 31-45
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  • 9
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    Behavior of Vortex Systems (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Progressive application of the Kutta-Joukowsky theorem to the relationship between airfoil lift and circulation affords a number of formulas concerning the conduct of vortex systems. The application of this line of reasoning to several problems of airfoil theory yields an insight into many hitherto little observed relations. This report is confined to plane flow, hence all vortex filaments are straight and mutually parallel (perpendicular to the plane of flow).
    Keywords: Aerodynamics
    Type: NACA-TM-713
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  • 10
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    On the Elementary Relation Between Pitch, Slip, and Propulsive Efficiency (1920)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-TM-1
    Format: application/pdf
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