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  • Inorganic Chemistry  (7,255)
  • Aircraft Design, Testing and Performance  (32)
  • 1935-1939  (3,387)
  • 1930-1934  (3,900)
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Keywords
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Year
  • 1
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    N.A.C.A. Stall-Warning Device (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: With some airplanes the approach to the stall is accompanied by changes in the behavior, such as tail buffeting or changes in the control characteristics of the airplane so that the pilot obtains a warning of the impending stall. Vith other airplanes it is possible to approach the stall without any perceptible warning other than the reading of the air-speed meter, in which case the danger of inadvertent stalling is considerably greater. Although it is not within the scope of this paper to discuss stalling characteristics, it is desired to point out that in general the danger of inadvertent stalling is greatest with those airplanes that behave worse when the stalling occurs; that is, with airplanes in which the stall starts at the wing tips. A warning of the impending stall is desirable in any case, but is particularly desirable with airplanes of the latter type.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-80
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: The pressure distribution on the fuselage of a midwing airplane model was measured in the NACA 8-foot high speed wind tunnel at speeds from 140 to 440 miles per hour for lift coefficients ranging from -0.2 to 1.0. The primary purpose of the tests was to provide data showing the air pressures on various parts of the fuselage for use in structural design. The data may also be used for the design of scoops and vents. The results show that the highest negative pressures occurred near the wing and were more dependent on the wing than on the fuselage. At high speeds, the magnitude of the pressure coefficients as predicted from pressure coefficients determined experimentally at low speeds by application of the theoretical factor 1/(square root)1-M(exp 2) (where M is the ratio of the air speed to the speed of sound in air) may misrepresent the actual conditions. At the points where the maximum negative pressures ocurred, however, the variation of the pressure coefficients was in good agreement with the theoretical factor, indicating that this factor may afford satisfactory predictions of critical speed, at least for fuselages similar to the shape tested.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-133
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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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  • 4
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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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  • 5
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    Preliminary Fatigue Studies on Aluminum Alloy Aircraft Girders (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Preliminary information on the complex subject of the fatigue strength of fabricated structural members for aircraft is presented in the test results obtained on several different types of airship girders subjected to axial tension and compression in a resonance fatigue machine. A description of this machine as well as numerous photographs of the fatigue failures are given. There is also presented an extended bibliography on the subject of fatigue strength.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-637
    Format: application/pdf
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  • 6
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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
    Format: application/pdf
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  • 7
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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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  • 8
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    A Flight Determination of the Moments of the YG-1B Tapered Blade Rotor about the Hub Trunnions (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: At the request of the Materiel Division, Wright Field, the National Advisory Committee for Aeronautics is conducting a program of flight tests on a Kellett YG-1B autogiro equipped with a new type of rotor blade. The new blades are tapered in both plan form. and thickness and are designed to avoid periodic blade twist. One phase of the investigation, involving determination of the moments of the resultant rotor force about the trunnions on which the hub is pivoted for control, has been completed. The results obtained are reported herein.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-X-1939
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Preliminary Full-Scale Wind-Tunnel Investigation of Wing Ducts for Radiators, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wing ducts for liquid-cooled engine radiators have been investigated in the N.A.C.A. full-scale wind tunnel on a large model airplane. Th e tests were made to determine the relative merits of several types of duct and radiator installations for an airplane of a particular des ign. In the test program the principal duct dimensions were system atically varied, and the results are therefore somewhat applicable to the general problems of wing duct design, although they should be co nsidered as preliminary and only indicative of the inherent possibil ities.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-88
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Relative Efficiencies and Design Charts for Various Engine-Propeller Combinations, Special Report (1936)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The relative efficiencies of various engine-propeller combinations were the subject of a study that covered the important flight conditions, particularly the take-off. Design charts that graphically correlate the various propeller parameters were prepared to facilitate the solution of problems and also to c1arify the conception of the relationships of the various engine-propeller design factors. It is shown that, among the many methods for improving the take-off thrust, the use of high-pitch, large-diameter controllable propellers turning at low rotational speeds is probably the most generally promising. With such a combination the take-off thrust may be further increased, at the expense of a small loss in cruising efficiency, by compromise designs wherein the pitch setting is slightly reduced and the diameter is further increased. The degree of compromise necessary to accomplish the maximum possible take-off improvement depends on such design factors as overspeeding and overboosting at take-off as well as depending on the design altitude. Both overspeeding and designing for altitude operation have the same effect on the take-off thrust as compromising in that the propulsive efficiency is increased thereby; boosting the engine, however, has the reverse effect on the propulsive efficiency, although the brake horsepower is increased.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-55
    Format: application/pdf
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