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  • 1
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    A discussion of certain problems connected with the design of hulls of flying boats and the use of general test data (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of a survey of problems encountered in applying general test data to the design of flying-boat hulls. It is shown how basic design features may be readily determined from special plots of test data. A study of the effect of the size of a flying boat on the probable limits to be covered by the general test data is included and recommendations for special tests and new methods of presenting test data for direct use in design are given.
    Type: NACA-TR-625
    Format: application/pdf
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  • 2
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    A new chart for estimating the absolute ceiling of an airplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is concerned with the derivation of a chart for estimating the absolute ceiling of an airplane. This chart may be used in conjunction with the usual curves of power required and power available as an accurate substitute for extended calculation, or it may be used in the estimation of absolute ceiling when power curves are not available.
    Type: NACA-TR-368
    Format: application/pdf
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  • 3
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    The calculation of take-off run (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A comparatively simple method of calculating length of take-off run is developed from the assumption of a linear variation in net accelerating force with air speed and it is shown that the error involved is negligible.
    Type: NACA-TR-450
    Format: application/pdf
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  • 4
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    Tests on airplane fuselages, floats and hulls (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is a compilation of test data on airplane fuselages, nacelles, airship cars, seaplane floats, and seaplane hulls, prepared by the Bureau of Aeronautics, at the requests of the National Advisory Committee for Aeronautics. The discussion of the data includes the derivation of a scale correction curve to be used in obtaining the full scale drag. Composite curves of drag and L/D for floats and hulls are also given. (author)
    Type: NACA-TR-236
    Format: application/pdf
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  • 5
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    Some fundamental considerations in regard to the use of power in landing an airplane (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is concerned with the effect of power on landing speed and apparent maximum lift coefficient. It is shown that when secondary effects are neglected, the maximum available increase in lift due to power is equal to the thrust being developed. If the increase in lift due to power is expressed in coefficient form, very high values may be shown under conditions which, on analysis, are found to be wholly impracticable in flight.
    Type: NACA-TN-692
    Format: application/pdf
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  • 6
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    A study of flying-boat take-off (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is shown that the normal resistance curve for a flying boat may be approximated by two straight lines. The equations for take-off distance and time, derived from this approximation, are applied to a series of flying boats and the resulting factors are plotted in non dimensional form in a series of charts. Take-off performances from the charts are shown to be in good agreement with step-by-step integrations. Some applications of the charts to the solution of general design problems are included.
    Type: NACA-TN-643
    Format: application/pdf
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  • 7
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    Notes on the Construction and Testing of Model Airplanes (1922)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Here, it is shown that the construction of an airplane model can and should be simplified in order to obtain the most reliable test data. General requirements for model construction are given, keeping in mind that the general purpose of wind tunnel tests on a model airplane is to obtain the aerodynamic characteristics, the static balance, and the efficiency of controls for the particular combination of wings, tail surfaces, fuselage, and landing gear employed in the design. These parts must be exact scale reproductions. Any appreciable variation from scale reproduction must be in the remaining parts of the model, i.e., struts, wires, fittings, control horns, radiators, engines, and the various attachments found exposed to the wind in special airplanes. Interplane bracing is discussed in some detail.
    Type: NACA-TN-82
    Format: application/pdf
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  • 8
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    Effect of aerofoil aspect ratio on the slope of the lift curve (1922)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: On of the most important characteristics of an airfoil is the rate of change of lift with angle of attack, (sup dC)L/d alpha. This factor determines the effectiveness of a tail plane in securing static longitudinal stability. The application of the Gottingen formulas given here for calculating the variation of (sup Dc)L/d alpha with aspect ratio should be of interest to many aeronautical engineers. For the convenience of the engineer, a set of curves calculated by the method set forth here are given in graphical form. Also, the observed values of (sup dC)L/d alpha for the same airfoil at various aspect ratios follow the calculated curves closely.
    Type: NACA-TN-79
    Format: application/pdf
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  • 9
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    Simple formula for estimating airplane ceilings (1922)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aeronautical engineer often has occasion to estimate the absolute ceiling of an airplane for which a detailed performance calculation is out of the question. In such cases it is customary to use either empirical performance charts or formulae. The performance charts given in several of the recent works on aeronautics are satisfactory so long as the airplane under consideration does not depart too far from the average in its characteristics. The formulae, with one exception, are no better. Given here is that exception, with indications of which terms of the formula may be neglected without seriously affecting the results, thus simplifying the task.
    Type: NACA-TN-103
    Format: application/pdf
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  • 10
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    The Determination of Downwash (1921)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is obvious that, in accordance with Newton's second law, the lift on an aerofoil must be equal to the vertical momentum communicated per second to the air mass affected. Consequently a lifting aerofoil in flight is trailed by a wash which has a definite inclination corresponding to the factors producing the lift. It is thought that sufficient data, theoretical and experimental, are now available for a complete determination of this wash with respect to the variation of its angle of inclination to the originating aerofoil and with respect to the law which governs its decay in space.
    Type: NACA-TN-42
    Format: application/pdf
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