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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1936
 Serial/Series Title: NACA Technical Reports
 Collection: Technical Report Archive and Image Library
Aerodynamic characteristics of a wing with Fowler flaps including flap loads, downwash, and calculated effect on take-off

Aerodynamic characteristics of a wing with Fowler flaps including flap loads, downwash, and calculated effect on take-off

Date: January 1, 1936
Creator: Platt, Robert C
Description: This report presents the results of wind tunnel tests of a wing in combination with each of three sizes of Fowler flap. The purpose of the investigation was to determine the aerodynamic characteristics as affected by flap chord and position, the air loads on the flaps, and the effect of flaps on the downwash.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of wings with cambered external airfoil flaps, including lateral control, with a full-span flap

Aerodynamic characteristics of wings with cambered external airfoil flaps, including lateral control, with a full-span flap

Date: January 1, 1936
Creator: Platt, Robert C
Description: The results of a wind-tunnel investigation of the NACA 23012, the NACA 23021, and the Clark Y airfoils, each equipped with a cambered external-airfoil flap, are presented in this report. The purpose of the research was to determine the relative merit of the various airfoils in combination with the cambered flap and to investigate the use of the flap as a combined lateral-control and high-lift device.
Contributing Partner: UNT Libraries Government Documents Department
Air flow in a separating laminar boundary layer

Air flow in a separating laminar boundary layer

Date: January 1, 1936
Creator: Schubauer, G B
Description: The speed distribution in a laminar boundary layer on the surface of an elliptic cylinder, of major and minor axes 11.78 and 3.98 inches, respectively, has been determined by means of a hot-wire anemometer. The direction of the impinging air stream was parallel to the major axis. Special attention was given to the region of separation and to the exact location of the point of separation. An approximate method, developed by K. Pohlhausen for computing the speed distribution, the thickness of the layer, and the point of separation, is described in detail; and speed-distribution curves calculated by this method are presented for comparison with experiment.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-pressure tables based on the United States standard atmosphere

Altitude-pressure tables based on the United States standard atmosphere

Date: January 1, 1936
Creator: Brombacher, W G
Description: This report is a revision of the altitude pressure tables of the United States standard atmosphere given in Technical Report No. 246. The altitude range has been extended from 50,000 to 80,000 feet.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of 2-spar cantilever wings with special reference to torsion and load transference

Analysis of 2-spar cantilever wings with special reference to torsion and load transference

Date: January 1, 1936
Creator: Kuhn, Paul
Description: This report deals with the analysis of 2-spar cantilever wings in torsion, taking cognizance of the fact that the spars are not independent, but are interconnected by ribs and other structural members. The principles of interaction are briefly explained, showing that the mutual relief action occurring depends on the "pure torsional stiffness" of the wing cross section. Various practical methods of analysis are outlined. The "Friedrichs-Von Karman equations" are shown to require the least amount of labor. Numerical examples by the several methods of analysis are given and the agreement between the calculation and experiment is shown.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of longitudinal stability in power-off flight with charts for use in design

An analysis of longitudinal stability in power-off flight with charts for use in design

Date: January 1, 1936
Creator: Zimmerman, Charles H
Description: This report presents a discussion of longitudinal stability in gliding flight together with a series of charts with which the stability characteristics of any airplane may be readily estimated.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of the NACA 23012 airfoil from tests in the full-scale and variable-density tunnels

Characteristics of the NACA 23012 airfoil from tests in the full-scale and variable-density tunnels

Date: January 1, 1936
Creator: Jacobs, Eastman N
Description: This report gives the results of tests in the NACA full-scale and variable-density tunnels of a new wing section, the NACA 23012, which is one of the more promising of an extended series of related airfoils recently developed. The tests were made at several values of the Reynolds number between 1,000,000 and 8,000,000. The new airfoil develops a reasonably high maximum lift and a low profile drag, which results in an unusually high value of the speed-range index. In addition, the pitching-moment coefficient is very small. The superiority of the new section over well-known and commonly used sections of small camber and moderate thickness is indicated by making a direct comparison with variable-density tests of the NACA 2212, the well-known NACA family airfoil that most nearly resembles it. The superiority is further indicated by comparing the characteristics with those obtained from full-scale-tunnel tests of the Clark y airfoil.
Contributing Partner: UNT Libraries Government Documents Department
A comparison of fuel sprays from several types of injection nozzles

A comparison of fuel sprays from several types of injection nozzles

Date: January 1, 1936
Creator: Lee, Dana W
Description: This report presents the tests results of a series of tests made of the sprays from 14 fuel injection nozzles of 9 different types, the sprays being injected into air at atmospheric density and at 6 and 14 times atmospheric density. High-speed spark photographs of the sprays from each nozzle at each air density were taken at the rate of 2,000 per second, and from them were obtained the dimensions of the sprays and the rates of spray-tip penetration. The sprays were also injected against plasticine targets placed at different distances from the nozzles, and the impressions made in the plasticine were used as an indication of the distribution of the fuel within the spray. Cross-sectional sketches of the different types of sprays are given showing the relative sizes of the spray cores and envelopes. The characteristics of the sprays are compared and discussed with respect to their application to various types of engines.
Contributing Partner: UNT Libraries Government Documents Department
Distribution and regularity of injection from a multicylinder fuel-injection pump

Distribution and regularity of injection from a multicylinder fuel-injection pump

Date: January 1, 1936
Creator: Rothrock, A M
Description: This report presents the results of performance test conducted on a six-cylinder commercial fuel-injection pump that was adjusted to give uniform fuel distribution among the cylinders at a throttle setting of 0.00038 pound per injection and a pump speed of 750 revolutions per minute. The throttle setting and pump speed were then varied through the operating range to determine the uniformity of distribution and regularity of injection.
Contributing Partner: UNT Libraries Government Documents Department
The drag of airplane wheels, wheel fairings, and landing gears II : nonretractable and partly retractable landing gears

The drag of airplane wheels, wheel fairings, and landing gears II : nonretractable and partly retractable landing gears

Date: January 1, 1936
Creator: Biermann, David
Description: This is the second report giving the results obtained in the NACA 20-foot wind tunnel on the drag due to landing gears. The present report gives the results of tests of nonretractable and partly retractable landing gears intended for heavier low-wing monoplanes of the transport and bomber type.
Contributing Partner: UNT Libraries Government Documents Department
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