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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1935
 Serial/Series Title: NACA Technical Notes
 Collection: Technical Report Archive and Image Library
The 6-foot-4-inch wind tunnel at the Washington Navy Yard

The 6-foot-4-inch wind tunnel at the Washington Navy Yard

Date: August 1, 1935
Creator: Desmond, G L
Description: The 6-foot-4-inch wind tunnel and its auxiliary equipment has proven itself capable of continuous and reliable output of data. The real value of the tunnel will increase as experience is gained in checking the observed tunnel performance against full-scale performance. Such has been the case of the 8- by 8-foot tunnel, and for that reason the comparison in the calibration tests have been presented.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several airfoils of low aspect ratio

Aerodynamic characteristics of several airfoils of low aspect ratio

Date: August 1, 1935
Creator: Zimmerman, C H
Description: This paper presents the results of wind-tunnel tests of several airfoils of low aspect ratio. The airfoils included three circular Clark Y airfoils with different amounts of dihedral, two Clark Y airfoils with slots in their portions, and three flat-plate airfoils. Lift, drag, and pitching-moment characteristics of the slotted airfoils with slots open and closed; pitching moment characteristics of one of the slotted airfoils with slots open and closed; and lift characteristics of the flat-plate airfoils are included. The results reveal a definite improvement of lift, drag, and pitching-moment characteristics with increase in dihedral of the circular Clark Y wing. Lift characteristics near the stall were found to depend markedly on the shape of the extreme tip but were not greatly affected by slots through the after portion of the airfoils. Changes in plan form of the flat-plate airfoils gave erroneous indications of the effect to be expected from changes in plan form of an airfoil of Clark Y section. The minimum drag characteristics of the circular Clark Y airfoils were found to be substantially the same as for a Clark Y airfoil of conventional aspect ratio.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic drag of flying-boat hull model as measured in the NACA 20-foot wind tunnel I.

The aerodynamic drag of flying-boat hull model as measured in the NACA 20-foot wind tunnel I.

Date: April 1, 1935
Creator: Hartman, Edwin P
Description: Measurements of aerodynamic drag were made in the 20-foot wind tunnel on a representative group of 11 flying-boat hull models. Four of the models were modified to investigate the effect of variations in over-all height, contours of deck, depth of step, angle of afterbody keel, and the addition of spray strips and windshields. The results of these tests, which cover a pitch-angle range from -5 to 10 degrees, are presented in a form suitable for use in performance calculations and for design purposes.
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The aerodynamic forces and moments on a spinning model of the F4B-2 airplane as measured by the spinning balance

The aerodynamic forces and moments on a spinning model of the F4B-2 airplane as measured by the spinning balance

Date: February 1, 1935
Creator: Bamber, M J
Description: The aerodynamic forces and moments on a 1/12-scale model of the F4B-2 airplane were measured with the spinning balance in nine spinning attitudes with three sets of tail surfaces, namely, F4B-2 surfaces; F4B-4 fin and rudder with rectangular stabilizer; and with all tail surfaces removed. In one of these attitudes measurements were made to determine the effect upon the forces and moments of independent and of simultaneous displacement of the rudder and elevator for two of the sets of tail surfaces. Additional measurements were made for a comparison of model and full-scale data for six attitudes that were determined from flight tests with various control settings. The characteristics were found to vary in the usual manner with angle of attack and sideslip. The F4B-2 surfaces were quite ineffective as a source of yawing moments. The F4B-4 fin and F4B-2 stabilizer gave a greater damping yawing moment when controls were against the spin than did the F4B-2 surfaces but otherwise there was little difference. Substitution of a rectangular stabilizer for the F4B-2 stabilizer made no appreciable difference in the coefficient. Further comparisons with other airplane types are necessary before final conclusions can be drawn as to the relations between model and ...
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Analysis of a strut with a single elastic support in the span, with applications to the design of airplane jury-strut systems

Analysis of a strut with a single elastic support in the span, with applications to the design of airplane jury-strut systems

Date: May 1, 1935
Creator: Schwartz, A Murray
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Application of the Von Karman-millikan Laminar Boundary-layer Theory and Comparison With Experiment

An Application of the Von Karman-millikan Laminar Boundary-layer Theory and Comparison With Experiment

Date: October 1, 1935
Creator: Doenhoff, A. E. V.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An application of the von Karman-Millikan laminar boundary-layer theory and comparison with experiment

An application of the von Karman-Millikan laminar boundary-layer theory and comparison with experiment

Date: October 1, 1935
Creator: Von Doenhoff, Albert E
Description: The von Karman-Millikan theory of laminar boundary layers presented in NACA Technical Report No. 504 is applied to the laminar boundary layer about an elliptic cylinder on which boundary-layer and pressure-distribution measurements were made. An outline of the procedure of the von Karman-Millikan method is given. Good agreement is obtained between the calculated and experimental results, indicating that the method may be applied generally to the laminar boundary layer about any body provided that an experimentally determined pressure distribution is available. It appears that for all Reynolds Number above 24,000 the separation point for the elliptic cylinder should occur at a constant distance behind the point of minimum pressure, provided that the boundary layer does not become turbulent.
Contributing Partner: UNT Libraries Government Documents Department
Bending stresses due to torsion in cantilever box beams

Bending stresses due to torsion in cantilever box beams

Date: June 1, 1935
Creator: Kuhn, Paul
Description: The paper beings with a brief discussion on the origin of the bending stresses in cantilever box beams under torsion. A critical survey of existing theory is followed by a summary of design formulas; this summary is based on the most complete solution published but omits all refinements considered unnecessary at the present state of development. Strain-gage tests made by NACA to obtained some experimental verification of the formulas are described next. Finally, the formulas are applied to a series of box beams previously static-tested by the U.S. Army Air Corps; the results show that the bending stresses due to torsion are responsible to a large extent for the free-edge type of failure frequently experienced in these tests.
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Calculations of the effect of wing twist on the air forces acting on a monoplane wing

Calculations of the effect of wing twist on the air forces acting on a monoplane wing

Date: January 1, 1935
Creator: Datwyler, G
Description: A method is presented for calculating the aerodynamic forces on a moncylane wing, taking into account the elastic twisting of the wing due to these forces. The lift distribution along the span is calculated by the formulas of Amstutz as a function of the geometrical characteristics of the wing and of the twist at stations 60 and 90 percent of the semispan. The twist for a given lift distribution is calculated by means of influence lines. As a numerical example, the forces on a Swiss military D.2V airplane are calculated. Comparisons with the strip method and with the ordinary stress-analysis method are also given.
Contributing Partner: UNT Libraries Government Documents Department
Comparative tests of Pitot-static tubes

Comparative tests of Pitot-static tubes

Date: November 1, 1935
Creator: Merriam, Kenneth G
Description: Comparative tests were made on seven conventional Pitot-static tubes to determine their static, dynamic, and resultant errors. The effect of varying the dynamic opening, static opening, wall thickness, and inner-tube diameter was investigated. Pressure-distribution measurements showing stem and tip effects were also made. A tentative design for a standard Pitot-static tube for use in measuring air velocity is submitted.
Contributing Partner: UNT Libraries Government Documents Department
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