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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 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 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
The aerodynamic aspect of wing-fuselage fillets

The aerodynamic aspect of wing-fuselage fillets

Date: February 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 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: 1935
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 several airfoils of low aspect ratio

Aerodynamic characteristics of several airfoils of low aspect ratio

Date: August 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.
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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: 1935
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
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 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 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 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 ...
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The aeronautical laboratory of the Stockholm Technical Institute

The aeronautical laboratory of the Stockholm Technical Institute

Date: March 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 flow around finned cylinders

Air flow around finned cylinders

Date: November 7, 1935
Creator: Brevoort, M J & Rollin, Vern G
Description: Report presents the results of a study made to determine the air-flow characteristics around finned cylinders. Air-flow distribution is given for a smooth cylinder, for a finned cylinder having several fin spacings and fin widths, and for a cylinder with several types of baffle with various entrance and exit shapes. The results of these tests show: that flow characteristics around a cylinder are not so critical to changes in fin width as they are to fin spacing; that the entrance of the baffle has a marked influence on its efficiency; that properly designed baffles increase the air flow over the rear of the cylinder; and that these tests check those of heat-transfer tests in the choice of the best baffle.
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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 & Bogert, Reid
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (20th).administrative report including Technical Report nos. 475 to 507

Annual report of the National Advisory Committee for Aeronautics (20th).administrative report including Technical Report nos. 475 to 507

Date: 1935
Creator: unknown
Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
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 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.
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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 1935
Creator: Doenhoff, A. E. V.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The bending of beams with thin tension flanges

The bending of beams with thin tension flanges

Date: March 1, 1935
Creator: Cicala, Placido
Description: This report analyzes the action of a cantilever T beam with a tension flange so thin it can only carry tensile stresses.
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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.
Contributing Partner: UNT Libraries Government Documents Department
Boulton Paul p.71A commercial airplane (British) : a two-engine biplane

Boulton Paul p.71A commercial airplane (British) : a two-engine biplane

Date: March 1, 1935
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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
Combustion in a bomb with a fuel-injection system

Combustion in a bomb with a fuel-injection system

Date: January 1, 1935
Creator: Cohn, Mildred & Spencer, Robert C
Description: Fuel injected into a spherical bomb filled with air at a desired density and temperature could be ignited with a spark a few thousandths of a second after injection, an interval comparable with the ignition lag in fuel-injection engines. The effect of several variables on the extent and rate of combustion was investigated: time intervals between injection and ignition of fuel of 0.003 to 0.06 second and one of 5 minutes; initial air temperatures of 100 degrees C. to 250 degrees C.; initial air densities equivalent to 5, 10, and 15 absolute atmospheres pressure at 100 degrees C.; and air-fuel ratios of 5 to 25.
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Comparative tests of Pitot-static tubes

Comparative tests of Pitot-static tubes

Date: November 1, 1935
Creator: Merriam, Kenneth G & Spaulding, Ellis R
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.
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The compressibility bubble

The compressibility bubble

Date: October 1, 1935
Creator: Stack, John
Description: Simultaneous air-flow photographs and pressure-distribution measurements have been made of the NACA 4412 airfoil at high speeds in order to determine the physical nature of the compressibility bubble. The flow photographs were obtained by the Schlieren method and the pressures were simultaneously measured for 54 stations on the 5-inch-chord wing by means of a multiple-tube photographic manometer. Pressure-measurement results and typical Schlieren photographs are presented. The general nature of the phenomenon called the "compressibility bubble" is shown by these experiments. The source of the increased drag is the compression shock that occurs, the excess drag being due to the conversion of a considerable amount of the air-stream kinetic energy into heat at the compression shock.
Contributing Partner: UNT Libraries Government Documents Department
Computation of the two-dimensional flow in a laminar boundary layer

Computation of the two-dimensional flow in a laminar boundary layer

Date: January 1, 1935
Creator: Dryden, Hugh L
Description: A comparison is made of the boundary-layer flow computed by the approximate method developed by K. Pohlhausen with the exact solutions which have been published for several special cases. A modification of Pohlhausen's method has been developed which extends the range of application at the expense of some decrease in the accuracy of the approximations.
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A deflection formula for single-span beams of constant section subjected to combined axial and transverse loads

A deflection formula for single-span beams of constant section subjected to combined axial and transverse loads

Date: September 1, 1935
Creator: Burke, Walter F
Description: In this paper there is presented a deflection formula for single-span beams of constant section subjected to combined axial and transverse loads of the types commonly encountered in airplane design. The form of the equation is obtainable by dimensional analysis. Tables and curves of the non dimensional coefficients are appended to facilitate the use of the formula. The equation is applied to the determination of the spring constant of a beam. Tables and curves are presented to show the variation of the spring constant with changes in the axial load and position along the beam.
Contributing Partner: UNT Libraries Government Documents Department
The Denis-Gruson six-component wind-tunnel balance

The Denis-Gruson six-component wind-tunnel balance

Date: July 1, 1935
Creator: unknown
Description: The 6.C.1 balance is the first fully automatic balance assuring a continuous and simultaneous record of the aerodynamic characteristics of an airfoil in a wind tunnel. Because of the rapidity of the measurements a complete polar (six components) requires only about three minutes of wind, that is to say, of motive power, which is of interest for wind tunnels with high efficiency factors and may lead to the economical design of large size wind tunnels.
Contributing Partner: UNT Libraries Government Documents Department
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