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 Decade: 1940-1949
 Collection: National Advisory Committee for Aeronautics Collection
Icing properties of noncyclonic winter stratus clouds

Icing properties of noncyclonic winter stratus clouds

Date: September 1, 1947
Creator: Lewis, W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Observations of icing conditions encountered in flight during 1948

Observations of icing conditions encountered in flight during 1948

Date: June 1, 1949
Creator: Lewis, W. & Hoecker, W. H., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Electric Thrust Meter Suitable for Flight Investigation of Propellers

An Electric Thrust Meter Suitable for Flight Investigation of Propellers

Date: May 9, 1949
Creator: Perkins, Porter J., Jr. & Millenson, Morton B.
Description: A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.
Contributing Partner: UNT Libraries Government Documents Department
A review of instruments developed for the measurement of the meteorological factors conductive to aircraft icing

A review of instruments developed for the measurement of the meteorological factors conductive to aircraft icing

Date: April 26, 1949
Creator: Jones, A. R. & Lewis, W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Model tests of a wing-duct system for auxiliary air supply

Model tests of a wing-duct system for auxiliary air supply

Date: January 1, 1941
Creator: Bierman, D. & Corson, B. W., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The column strength of aluminum alloy 75S-T extruded shapes

The column strength of aluminum alloy 75S-T extruded shapes

Date: January 1, 1946
Creator: Holt, Marshall & Leary, J R
Description: Because the tensile strength and tensile yield strength of alloy 75S-T are appreciably higher than those of the materials used in the tests leading to the use of the straight-line column curve, it appeared advisable to establish the curve of column strength by test rather than by extrapolation of relations determined empirically in the earlier tests. The object of this investigation was to determine the curve of column strength for extruded aluminum alloy 75S-T. In addition to three extruded shapes, a rolled-and-drawn round rod was included. Specimens of various lengths covering the range of effective slenderness ratios up to about 100 were tested.
Contributing Partner: UNT Libraries Government Documents Department
Stress analysis of columns and beam columns by the photoelastic method

Stress analysis of columns and beam columns by the photoelastic method

Date: March 1, 1946
Creator: Ruffner, B F
Description: Principles of similarity and other factors in the design of models for photoelastic testing are discussed. Some approximate theoretical equations, useful in the analysis of results obtained from photoelastic tests are derived. Examples of the use of photoelastic techniques and the analysis of results as applied to uniform and tapered beam columns, circular rings, and statically indeterminate frames, are given. It is concluded that this method is an effective tool for the analysis of structures in which column action is present, particularly in tapered beam columns, and in statically indeterminate structures in which the distribution of loads in the structures is influenced by bending moments due to axial loads in one or more members.
Contributing Partner: UNT Libraries Government Documents Department
A Simple Method of Estimating the Subsonic Lift and Damping in Roll of Sweptback Wings

A Simple Method of Estimating the Subsonic Lift and Damping in Roll of Sweptback Wings

Date: April 1, 1949
Creator: Polhamus, Edward C.
Description: A method of modifying existing correction factors of lifting-surface theory to account approximately for the effects of sweep was derived, and these factors were applied to existing lifting-line theories for the lift and damping in roll of swept wings. Despite the simplicity of the resulting formulas the agreement with experimental data for low speeds is very good. The equation for lift is expressed entirely in terms of the geometric characteristics of the wing and the section-lift-curve; the necessity for any charts is thereby eliminated. The equation for the damping in roll, however, requires a chart for the determination of the effective lateral center of pressure for rolling moment due to rolling. If the Glauert-Prandtl transformation is used, the formulas obtained can be applied to swept wings at subsonic speeds below the critical speed.
Contributing Partner: UNT Libraries Government Documents Department
Investigation at low speeds of the effect of aspect ratio and sweep on rolling stability derivatives of untapered wings

Investigation at low speeds of the effect of aspect ratio and sweep on rolling stability derivatives of untapered wings

Date: March 1, 1949
Creator: Goodman, Alex & Fisher, Lewis R.
Description: A low scale wind tunnel investigation was conducted in rolling flow to determine the effects of aspect ratio and sweep (when varied independently) on the rolling stability derivatives for a series of untapered wings. Test results indicate that when the aspect ratio was held constant, an increase in the sweepback angle caused a significant reduction in the damping in roll at low lift coefficients for only the higher aspect ratios that were tested. This result was in agreement with available swept wing theory which indicated no effect of sweep for aspect ratios near zero. The result of the linear theory that the damping in roll is independent of lift coefficient and that the yawing moment and lateral force due to rolling are directly proportional to the lift coefficient was found to be valid for only a very limited lift coefficient range when the wings were highly swept. For such wings, the damping was found to increase in magnitude and the yawing moment due to rolling, to change from negative to positive at moderate lift coefficients. The effect of wing tip suction, not acounted for by present theory, was found to be very important with regard to the yawing moment due ...
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of drag reduction in maintaining the laminar boundary layer by suction

Theoretical investigation of drag reduction in maintaining the laminar boundary layer by suction

Date: June 1, 1947
Creator: Ulrich, A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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