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  • General Chemistry  (3,654)
  • Aircraft Design, Testing and Performance  (10)
  • Aerodynamics  (6)
  • 1930-1934  (3,670)
Collection
Keywords
Publisher
Years
Year
  • 1
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    Identification of Aircraft Tubing by Rockwell Test (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Seamless steel tubing is today the principal material of construction for aircraft. The commercial grade of tubing containing about 0.10 to 0.20% carbon at first used is being superseded by two grades which are approved by the army and navy, and which are also becoming standard for commercial airplanes.
    Keywords: Aircraft Design, Testing and Performance
    Type: AD-B204801 , NASA-TM-111285 , NACA-TN-342 , NAS 1.15:111285
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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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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    NASA TECHNICAL REPORTS
  • 3
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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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    NASA TECHNICAL REPORTS
  • 4
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    Riveting in Metal Airplane Construction. Part I : Riveting Methods and Equipment in German Metal Airplane Construction (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A survey of methods and equipment used in the riveting of German aircraft. Includes descriptions and illustrations.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-596
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Wind Tunnel of the Bucharest Polytechnic Institute (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the Bucharest wind tunnel and presents numerous photographs and diagrams. The wind tunnel is of the closed- circuit type, the return being symmetrical with respect t o the longitudinal axis of the tunnel. Th e tunnel is of the horizontal type with a diameter of 3. 2 m (10. 5-ft.) a t the beginning of the entrance cone, and 1.5 m ( 4,92 ft.) at the entrance to the test chamber. The latter, 2 m (6.56 ft.) long, may be either of the open-jet type or enclosed in a cylindrical housing.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-651
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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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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    NASA TECHNICAL REPORTS
  • 7
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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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
    Format: application/pdf
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  • 9
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    Wings with Variable Camber and Slots (1933)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Investigations with a view to increasing the lift coefficient of a wing, without greatly increasing the C(sub x min), are chiefly related to the important question of the maximum speed range.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA Misc. Paper No. 37
    Format: application/pdf
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  • 10
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    A Complete Tank Test of a Model of a Flying-Boat Hull - N.A.C.A. Model No.11 (1933)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This note discusses the limitations of the conventional tank test of a seaplane model. The advantages of a complete test, giving the characteristics of the model at all speeds, loads, and trim angles in the useful range are pointed out. The data on N.A.C.A. Model No.11, obtained from a complete test, are presented and discussed. The results are analyzed to determine the best trim angle for each speed and load. The data for the best angles are reduced to non-dimensional form for ease of comparison and application. A practical problem using the characteristics of model no.11 is presented to show the method of calculating the take-off time and run of a seaplane from these data.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-464
    Format: application/pdf
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