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  • Other Sources  (16)
  • NASA Technical Reports  (16)
  • Aircraft Design, Testing and Performance  (10)
  • Aerodynamics  (6)
  • 1930-1934  (16)
Collection
  • Other Sources  (16)
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  • NASA Technical Reports  (16)
Keywords
Years
Year
  • 1
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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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  • 2
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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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  • 3
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    Resume of Present Data on Load Distribution on Slots and Flaps, Special Report (1934)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This report covers a study of the generally available data on load distribution on slots and flaps. The study was made by the National Advisory Committee for Aeronautics at the request of the Material Division, Army Air Corps to furnish information applicable to design criteria for slots and flaps of various types. The data are presented in three main sections: slots (Handley page type), auxiliary airfoils (fixed), and flaps.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-19
    Format: application/pdf
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  • 4
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    Preliminary Wind-Tunnel and Flight Tests of a Balanced Split Flap, Special Report (1934)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: One disadvantage that has been apparent in the operation of split flaps as used to date is the time and effort required to operate them. In this communication an investigation is being made of possible means for balancing them aerodynamically to make their operation easier. Several arrangements have been tested in the 7 by 210 foot wind tunnel, and the results of the wind-tunnel tests as well as preliminary flight tests on one of the more promising forms are given in this paper.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-23
    Format: application/pdf
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  • 5
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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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  • 6
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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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  • 7
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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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  • 8
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    Flight Tests on the Lateral Control of an Airplane having a Split Flap which Retracts Ahead of Conventional Ailerons, Special Report (1933)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Since the recent more or less extensive adoption of high-lift flaps on airplane wings, the problem of providing satisfactory lateral control without sacrificing a part of the span of the flaps has become one of some importance. The difficulties have been largely a matter of obtaining satisfactory rolling moments with a smoothly graduated action, together with sufficiently small control forces throughout the entire speed range. As part of an investigation including several different lateral-control arrangements to be used with split flaps, the tests reported in this paper were made on one arrangement in which conventional ailerons of narrow chord are used, and a split flap is retracted into the under surface of th wing forward of th ailerons. When the flap is retracted, the arrangement is as sketched in figure 1(a). If a simple form of split flap were used, hinged at its forward edge, the appearance when deflected would be as shown in figure 1(b). The flap if deflected with its leading edge remaining in this forward position would give somewhat less than three fourths of the lift increase of the same flap in the usual rear position. (See reference 1.). If, as shown in figure 1(c), the split flap ahead of th aileron is moved to the rear as the trailing=edge portion is deflected downward, a double advantage is obtained. The deflected flap can be located in the most effective region for high lift (reference 1), and the force required to deflect the flap is reduced. This is the arrangement used in the present tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-14
    Format: application/pdf
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  • 9
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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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  • 10
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    The Take-Off of Seaplanes, Based on a New Hydrodynamic Reduction Theory (1931)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The interpretation of the take-off resistance of seaplane floats by model test involves a problem in mechanics, the solution of which forms the basis of this report. The comparison of three float forms is confined to an angle = 5 degree trim run in order to preserve the clearness of the arrangement. But for complete comparison the corresponding curves for several trim runs should be included.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-621 , Zeitschrift fur Flugtechnik und Motorluftschiffahrt; 22; 8-12; 1
    Format: text
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  • 11
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    Estimated Effect of Ring Cowl on the Climb and Ceiling of an Airplane, Special Report (1931)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Although the application of a ring cowl to an airplane with an air-cooled engine increases the maximum L/D and the high speed to an appreciable extent, the performance in climb and ceiling is not increased as much as one would expect without analyzing the conditions. When a ring cowl is installed on an airplane, the propeller is set at a higher pitch to allow the engine to turn its rated r.p.m. at the increased high speed. V/nD is increased and the propeller efficiency at high speed is increased slightly. The ratio of r.p.m. at climbing speed, V(sub c) , to the r.p.m. at maximum speed, V (sub m) is dependent upon the ratio of V(sub c) to V(sub m). The increase in V(sub c) for all airplane with ring cowl i s not as great as the increase in V(sub m), so that the ratio V(sub c)/V(sub m) is less than for the airplane without ring. Consequently the r.p.m. and full throttle thrust power available are less at V(sub c) for the airplane with ring cowl and in spite of the increase in L/D due to the installation of the ring, the excess thrust power available for climbing is not appreciably changed. The same method of reasoning accounts for the small increase in absolute ceiling in spite of a large increase in L/D maximum.
    Keywords: Aerodynamics
    Type: NACA-SR-3A , NACA Misc. Paper No. 26
    Format: application/pdf
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  • 12
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    Method of Determining the Weights of the Most Important Simple Girders (1931)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents a series of tables for the simple and more common types of girders, similar to the tables given in handbooks under the heading "Strength of Materials," for determining the moments, deflections, etc., of simple beams. Instead of the uniform cross section there assumed, the formulas given here apply only to girders of "uniform strength," i.e., it is assumed that a girder is so dimensioned that a given load subjects it to a uniform stress throughout its whole length. This principle is particularly applicable to very strong structures. Girders of uniform strength are the lightest girders conceivable, because any girder, all of whose members are stressed to the limit, can not be surpassed by a lighter girder, if the two girders have the same form. The weight G of a member of length l, cross section F and specific gravity gamma is: G = Flgamma.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-3B , Zeitschrift fur Flugtechnik und Motorluftechiffahrt (Magazine for Aeronautical Engineering and Motorluftechniffahrt); 22; 15; 456-463
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  • 13
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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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  • 14
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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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  • 15
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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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  • 16
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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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