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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1935
 Collection: National Advisory Committee for Aeronautics Collection
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 & Mccrary, J A
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
The 1934 contest for the Deutsch de la Meurthe trophy

The 1934 contest for the Deutsch de la Meurthe trophy

Date: February 1, 1935
Creator: Leglise, Pierre
Description: This report presents a description of the rules, history and new technical innovations in the Deutsch de la Meurthe Cup race of 1934.
Contributing Partner: UNT Libraries Government Documents Department
An aerodynamic analysis of the autogiro rotor with a comparison between calculated and experimental results

An aerodynamic analysis of the autogiro rotor with a comparison between calculated and experimental results

Date: January 1, 1935
Creator: Wheatley, John B
Description: This report presents an extension of the autogiro theory of Glauert and Lock in which the influence of a pitch varying with the blade radius is evaluated and methods of approximating the effect of blade tip losses and the influence of reversed velocities on the retreating blades are developed. A comparison of calculated and experimental results showed that most of the rotor characteristics could be calculated with reasonable accuracy, and that the type of induced flow assumed has a secondary effect upon the net rotor forces, although the flapping motion is influenced appreciably. An approximate evaluation of the effect of parasite drag on the rotor blades established the importance of including this factor in the analysis.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic aspect of wing-fuselage fillets

The aerodynamic aspect of wing-fuselage fillets

Date: February 1, 1935
Creator: Muttray, H
Description: Model tests prove the feasibility of enhancing the aerodynamic qualities of wing-fuselage fillets by appropriate design of fuselage and wing roots. Abrupt changes from maximum fuselage height to wing chord must be avoided and every longitudinal section of fuselage and wing roots must be so faired and arranged as to preserve the original lift distribution of the continuous wing. Adapting the fuselage to the curvilinear circulation of the wing affords further improvement. The polars of such arrangements are almost the same as those of the "wing alone," thus voiding the superiority of the high-wing type airplane known with conventional design.
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.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic effects of wing cut-outs

The aerodynamic effects of wing cut-outs

Date: January 1, 1935
Creator: Sherman, Albert
Description: In connection with the interference program being conducted in the NACA variable-density wind tunnel, an analysis was made of available material with the object of presenting a qualitative discussion on wing characteristics as affected by cut-outs and of determining means for their quantitative calculation.
Contributing Partner: UNT Libraries Government Documents Department
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 & Zimmerman, C H
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 ...
Contributing Partner: UNT Libraries Government Documents Department
The aeronautical laboratory of the Stockholm Technical Institute

The aeronautical laboratory of the Stockholm Technical Institute

Date: March 1, 1935
Creator: Malmer, Ivar
Description: This report presents a detailed analysis and history of the construction and operation of the aeronautical laboratory of the Stockholm Technical Institute. Engines and balances are discussed and experimental results are also given.
Contributing Partner: UNT Libraries Government Documents Department
Air conditions close to the ground and the effect on airplane landings

Air conditions close to the ground and the effect on airplane landings

Date: January 1, 1935
Creator: Thompson, F L; Peck, W C & Beard, A P
Description: This report presents the results of an investigation undertaken to determine the feasibility of making glide landings in gusty air. Wind velocities were measured at several stations between the ground and a height of 51 feet, and flight tests were made to determine the actual influence of gusts on an airplane gliding close to the ground.
Contributing Partner: UNT Libraries Government Documents Department
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