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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Technical Reports
 Collection: Technical Report Archive and Image Library
Wind-tunnel investigation of NACA 23012 airfoil with various arrangements of slotted flaps

Wind-tunnel investigation of NACA 23012 airfoil with various arrangements of slotted flaps

Date: January 1, 1939
Creator: Wenzinger, Carl J & Harris, Thomas A
Description: An investigation was made in the NACA 7 by 10-foot wind tunnel of a large-chord NACA 23012 airfoil with several arrangements of 25.66 percent chord slotted flaps to determine the section aerodynamic characteristics as affected by slot shape, flap shape, flap location, and flap deflection. The flap position for maximum lift, the polars for arrangements considered favorable for take-off and climb, and the complete section aerodynamic characteristics for selected optimum arrangements were determined. A discussion is given of the relative merits of the various arrangement for certain selected criterions. A comparison is made of a slotted flap on the NACA 23021 airfoil with a corresponding slotted flap previously developed for the NACA 23012 airfoil.
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Cooling on the front of an air-cooled engine cylinder in a conventional engine cowling

Cooling on the front of an air-cooled engine cylinder in a conventional engine cowling

Date: January 1, 1939
Creator: Brevoort, M J & Joyner, U T
Description: Measurements were made of the cooling on the fronts of model cylinders in a conventional cowling for cooling in both the ground and the cruising conditions. The mechanisms of front and rear cooling are essentially different. Cooling on the rear baffled part of the cylinders continually increases with increasing fin width. For the front of the cylinder, an optimum fin width was found to exist beyond which an increase in width reduced the heat transfer. The heat transfer coefficient on the front of the cylinders was larger on the side of the cylinder facing the propeller swirl than on the opposite side. This effect became more pronounced as the fin width was increased. These results are introductory to the study of front cooling and show the general effect of several test parameters.
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Experimental verification of the theory of oscillating airfoils

Experimental verification of the theory of oscillating airfoils

Date: January 1, 1939
Creator: Silverstein, Abe & Joyner, Upshur T
Description: Measurements have been made of the lift on an airfoil in pitching oscillation with a continuous-recording, instantaneous-force balance. The experimental values for the phase difference between the angle of attack and the lift are shown to be in close agreement with theory.
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Wind-Tunnel Investigation of an N.A.C.A. 23012 Airfoil with a Slotted Flap and Three Types of Auxiliary Flap

Wind-Tunnel Investigation of an N.A.C.A. 23012 Airfoil with a Slotted Flap and Three Types of Auxiliary Flap

Date: January 1, 1939
Creator: Wenzinger, Carl J & Gauvain, Willikam E
Description: A test installation was used in which an airfoil of 7-foot span was mounted vertically between the upper and the lower sides of the closed test section so that two-dimensional flow was approximated.
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Free-spinning wind-tunnel tests of a low-wing monoplane with systematic changes in wings and tails IV : effect of center-of-gravity location

Free-spinning wind-tunnel tests of a low-wing monoplane with systematic changes in wings and tails IV : effect of center-of-gravity location

Date: January 1, 1939
Creator: Seidman, Oscar & Neihouse, A I
Description: Eight wings and three tails, covering a wide range of aerodynamic characteristics, were independently ballasted so as to be interchangeable with no change in mass distribution. For each of the 24 resulting wing-tail combinations, observations were made of the steady spin for four control settings and of recoveries for five control manipulations. The results are presented in the form of charts comparing the spin characteristics. The tests are part of a general investigation being made in the NACA free-spinning tunnel to determine the effects of systematic changes in wing and tail arrangement upon the steady-spin and the recovery characteristics of a conventional low-wing monoplane for various load distributions.
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The effect of nacelle-propeller diameter ratio on body interference and on propeller and cooling characteristics

The effect of nacelle-propeller diameter ratio on body interference and on propeller and cooling characteristics

Date: January 1, 1939
Creator: Mchugh, James G & Derring, Eldridge H
Description: Report presents the results of an investigation conducted in the NACA 20-foot tunnel to determine the slipstream drag, the body interference, and the cooling characteristics of nacelle-propeller diameter. Four combinations of geometrically similar propellers and nacelles, mounted on standard wing supports, were tested with values of the ratio of nacelle diameter to propeller diameter of 0.25, 0.33, and 0.44.
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Surface heat-transfer coefficients of finned cylinders

Surface heat-transfer coefficients of finned cylinders

Date: January 1, 1939
Creator: Ellerbrock, Herman H , Jr & Biermann, Arnold E
Description: An investigation to determine and correlate the experimental surface heat-transfer coefficients of finned cylinders with different air-stream cooling arrangements was conducted at the Langley Memorial Aeronautical Laboratory from 1932 to 1938. The investigation covered the determination of the effect of fin width, fin space, fin thickness, and cylinder diameter on the heat transfer. Wind-tunnel tests were made in the free air stream with and without baffles and also with various devices for creating a turbulent air stream. Tests were also made with blower.
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Interference of Tail Surfaces and Wing and Fuselage from Tests of 17 Combinations in the N.A.C.A. Variable-Density Tunnel

Interference of Tail Surfaces and Wing and Fuselage from Tests of 17 Combinations in the N.A.C.A. Variable-Density Tunnel

Date: January 1, 1939
Creator: Sherman, Albert
Description: An investigation of the interference associated with tail surfaces added to wing-fuselage combinations was included in the interference program in progress in the NACA variable-density tunnel. The results indicate that, in aerodynamically clean combinations, the increment of the high-speed drag can be estimated from section characteristics within useful limits of accuracy. The interference appears mainly as effects on the downwash angle and as losses in the tail effectiveness and varies with the geometry of the combination. An interference burble, which markedly increases the glide-path angle and the stability in pitch before the actual stall, may be considered a means of obtaining satisfactory stalling characteristics for complete combination.
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Effects of elevator nose shape, gap, balance, and tabs on the aerodynamic characteristics of a horizontal tail surface

Effects of elevator nose shape, gap, balance, and tabs on the aerodynamic characteristics of a horizontal tail surface

Date: January 1, 1939
Creator: Goett, Harry J & Reeder, J P
Description: Results are presented showing the effects of gap, elevator, nose shape, balance, cut-out, and tabs on the aerodynamic characteristics of a horizontal tail surface tested in the NACA full-scale tunnel.
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Investigations on the incompletely developed plane diagonal-tension field

Investigations on the incompletely developed plane diagonal-tension field

Date: January 1, 1940
Creator: Kuhn, Paul
Description: This report presents the results of an investigation on the incompletely developed diagonal-tension field. Actual diagonal-tension beams work in an intermediate stage between pure shear and pure diagonal tension; the theory developed by wagner for diagonal tension is not directly applicable. The first part of the paper reviews the most essential items of the theory of pure diagonal tension as well as previous attempts to formulate a theory of incomplete diagonal tension. The second part of the paper describes strain measurement made by the N. A. C. A. to obtain the necessary coefficients for the proposed theory. The third part of the paper discusses the stress analysis of diagonal-tension beams by means of the proposed theory.
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