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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1934
 Serial/Series Title: NACA Technical Notes
 Collection: Technical Report Archive and Image Library
The aerodynamic analysis of the gyroplane rotating-wing system

The aerodynamic analysis of the gyroplane rotating-wing system

Date: March 1, 1934
Creator: Wheatley, John B
Description: An aerodynamic analysis of the gyroplane rotating-wing system is presented herein. This system consists of a freely rotating rotor in which opposite blades are rigidly connected and allowed to rotate or feather freely about their span axis. Equations have been derived for the lift, the lift-drag ratio, the angle of attack, the feathering angles, and the rolling and pitching moments of a gyroplane rotor in terms of its basic parameters. Curves of lift-drag ratio against lift coefficient have been calculated for a typical case, showing the effect of varying the pitch angle, the solidarity, and the average blade-section drag coefficient. The analysis expresses satisfactorily the qualitative relations between the rotor characteristics and the rotor parameters. As disclosed by this investigation, the aerodynamic principles of the gyroplane are sound, and further research on this wing system is justified.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of anemometer cups

Aerodynamic characteristics of anemometer cups

Date: February 1, 1934
Creator: Brevoort, M J & Joyner, U T
Description: The static lift and drag forces on three hemispherical and two conical cups were measured over a range of angles of attack from 0 degrees to 180 degrees and a range of Reynolds Numbers from very small up to 400,000. The problems of supporting the cup for measurement and the effect of turbulence were also studied. The results were compared with those of other investigators.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic effects of a split flap on the spinning characteristics of a monoplane model

Aerodynamic effects of a split flap on the spinning characteristics of a monoplane model

Date: December 1, 1934
Creator: Bamber, M J
Description: The investigation described in this report was made to determine the change in aerodynamic forces and moments produced by split flaps in a steady spin. The test were made with the spinning balance in the NACA 5-foot vertical wind tunnel. A low-wing monoplane model was tested with and without the split flaps in 12 spinning attitudes chosen to cover the probable spinning range. The changes in coefficients produced by adding the split flaps are given for longitudinal force, normal force, and rolling and yawing moments about body axes. The results obtained indicate that the use of split flaps on an airplane is unlikely, in any case, to have much beneficial effect on a spin, and it might make the spin dangerous. The change in the spin will depend upon the aerodynamic and inertia characteristics of the particular airplane. A dangerous condition is most likely to be attained with airplanes which are statically stable in yaw in the spinning attitude and which have large weights distributed along wings.
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Aerodynamic Investigation of a Cup Anemometer

Aerodynamic Investigation of a Cup Anemometer

Date: July 1934
Creator: Hubbard, John D. & Brescoll, George P.
Description: Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic rolling and yawing moments produced by floating wing-tip ailerons, as measured by spinning balance

Aerodynamic rolling and yawing moments produced by floating wing-tip ailerons, as measured by spinning balance

Date: March 1, 1934
Creator: Bamber, Millard J
Description: The investigation described in this report was made to determine the effectiveness of floating wing-tip ailerons as an airplane control in the spin. In these tests the ailerons, not being balanced, were set parallel to the axis of rotation, which is probably very nearly the attitude that balanced floating ailerons would assume in a spin. The tests were made with the spinning balance in the N.A.C.A. 5-foot vertical tunnel. The model was tested with and without the ailerons in 12 spinning attitudes chosen to cover the probable spinning range. Rolling- and yawing-moment coefficients are given as measured for the model with and without the ailerons, and computed values are given for the ailerons alone. The addition of floating wing-tip ailerons to the model doubled the rolling-moment coefficient and increased the yawing-moment coefficient by 0.05 and more. Both moments were in a sense to oppose the spin.
Contributing Partner: UNT Libraries Government Documents Department
The calculated effect of trailing-edge flaps on the take-off of flying boats

The calculated effect of trailing-edge flaps on the take-off of flying boats

Date: November 1, 1934
Creator: Parkinson, J E & Bell, J W
Description: The results of take-off calculations are given for an application of simple trailing-edge flaps to two hypothetical flying boats, one having medium wing and power loading and consequently considerable excess of thrust over total resistance during the take-off run, the other having high wing and power loading and a very low excess thrust. For these seaplanes the effect of downward flap settings was: (1) to increase the total resistance below the stalling speed, (2) to decrease the get-away speed, (3) to improve the take-off performance of the seaplane having considerable excess thrust, and (4) to hinder the take-off of the seaplane having low excess thrust. It is indicated that flaps would allow a decrease in the high angles of wing setting necessary with most seaplanes, provided that the excess thrust is not too low.
Contributing Partner: UNT Libraries Government Documents Department
Calculation of horsepower available : appendix to estimation of the variation of thrust horsepower with air speed

Calculation of horsepower available : appendix to estimation of the variation of thrust horsepower with air speed

Date: July 1, 1934
Creator: Ober, Shatswell
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison of several methods of measuring ignition lag in a compression-ignition engine

A comparison of several methods of measuring ignition lag in a compression-ignition engine

Date: January 1, 1934
Creator: Spanogle, J A
Description: The ignition lag of a fuel oil in the combustion chamber of a high speed compression-ignition engine was measured by three different methods. The start of injection of the fuel as observed with a Stoborama was taken as the start of the period of ignition lag in all cases. The end of the period of ignition lag was determined by observation of the appearance of incandescence in the combustion chamber, by inspection of a pressure-time card for evidence of pressure rise, and by analysis of the indicator card for evidence of the combustion of a small but definite quantity of fuel. A comparison of the values for ignition lags obtained by these three methods indicates that the appearance of incandescence is later than other evidences of the start of combustion, that visual inspection of a pressure-time diagram gives consistent and usable values with a minimum requirement of time and/or apparatus, and that analysis of the indicator card is not worth while for ignition lag alone.
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A complete tank test of a flying-boat hull with a pointed step -N.A.C.A. Model No. 22

A complete tank test of a flying-boat hull with a pointed step -N.A.C.A. Model No. 22

Date: February 1, 1934
Creator: Shoemaker, James M
Description: The results of a complete tank test of a model of a flying-boat hull of unconventional form, having a deep pointed step, are presented in this note. The advantage of the pointed-step type over the usual forms of flying-boat hulls with respect to resistance at high speeds is pointed out. A take-off example using the data from these tests is worked out, and the results are compared with those of an example in which the test data for a hull of the type in general use in the United States are applied to a flying boat having the same design specifications. A definite saving in take-off run is shown by the pointed-step type.
Contributing Partner: UNT Libraries Government Documents Department
A complete tank test of the hull of the Sikorsky S-40 flying boat - American Clipper Class

A complete tank test of the hull of the Sikorsky S-40 flying boat - American Clipper Class

Date: December 1, 1934
Creator: Dawson, John R
Description: The results of a complete test in the N.A.C.A. tank on a model of the hull of Sikorsky S-40 flying boat ('American Clipper') are reported. The test data are given in tables and curves. From these data non-dimensional coefficients are derived for use in take-off calculations and the take-off time and run for the S-40 are computed. The computed take-off time was obtained by the Sikorsky Aviation Corporation in performance tests of the actual craft.
Contributing Partner: UNT Libraries Government Documents Department
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