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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Collection: Technical Report Archive and Image Library
Accelerations in Landing with a Tricycle-Type Landing Gear

Accelerations in Landing with a Tricycle-Type Landing Gear

Date: February 1937
Creator: Jones, Robert T.
Description: In connection with the application of stable tricycle-type landing gears to transport airplanes, the question arises as to whether certain passengers may not experience relatively great accelerations in an emergency landing. Since the main landing wheels are behind the center of gravity in this type of gear, a hard-braked landing will cause immediate nosing down of the airplane and, when this motion is stopped due to the front wheel striking the ground, there will be some tendency for the rearmost passengers to be thrown out of their seats, The provided rough calculations are designed to show the magnitudes of the various reactions experienced in a severe landing under these circumstances.
Contributing Partner: UNT Libraries Government Documents Department
Accident Experience and Cost of Accidents in Washington Coal Mines

Accident Experience and Cost of Accidents in Washington Coal Mines

Date: November 1931
Creator: Ash, S. H.
Description: Report containing tables detailing cost of mining accidents in Washington state in comparison with other states.
Contributing Partner: UNT Libraries Government Documents Department
Accounting System and Office-Management Procedure for Medium-Size Metal Mines

Accounting System and Office-Management Procedure for Medium-Size Metal Mines

Date: 1934
Creator: Keller, Albert E.
Description: Report discussing an accounting system and management of office procedures design for medium-size metal mines, offered by the United States Bureau of Mines, to be more efficient in the mining industry.
Contributing Partner: UNT Libraries Government Documents Department
Accurate calculation of multispar cantilever and semicantilever wings with parallel webs under direct and indirect loading

Accurate calculation of multispar cantilever and semicantilever wings with parallel webs under direct and indirect loading

Date: March 1932
Creator: Sanger, Eugen
Description: In the present report the computation is actually carried through for the case of parallel spars of equal resistance in bending without direct loading, including plotting of the influence lines; for other cases the method of calculation is explained. The development of large size airplanes can be speeded up by accurate methods of calculation such as this.
Contributing Partner: UNT Libraries Government Documents Department
An accurate method of measuring the moments of inertia of airplanes

An accurate method of measuring the moments of inertia of airplanes

Date: October 1930
Creator: Miller, M P
Description: This note contains a description of an improved apparatus and procedure used by the NACA for determining the moments of inertia of airplanes. The method used, based on the pendulum theory, is similar to that previously used, but a recent investigation of its accuracy has resulted in the improvements described herein. The error, when using the new apparatus and procedure, has been found to be of the order of 1 per cent.
Contributing Partner: UNT Libraries Government Documents Department
Activation of hydrocarbons and the octane number

Activation of hydrocarbons and the octane number

Date: October 1939
Creator: Peschard, Marcel
Description: This report presents an examination of the history of research on engine knocking and the various types of fuels used in the investigations of this phenomenon. According to this report, the spontaneous ignition of hydrocarbons doped with oxygen follows the logarithmic law within a certain temperature range, but not above 920 degrees K. Having extended the scope of investigations to prove hydrocarbons, the curves of the mixtures burned by air should then be established by progressive replacement of pure iso-octane with heptane. Pentane was also examined in this report.
Contributing Partner: UNT Libraries Government Documents Department
Additional test data on static longitudinal stability

Additional test data on static longitudinal stability

Date: August 1934
Creator: Hubner, Walter
Description: The purpose of this investigation was to explore the influence of weights of the controls on the stability with elevator released. The available test data were extended to stability with elevator locked. In this connection the study of the propeller effect seemed of vital importance.
Contributing Partner: UNT Libraries Government Documents Department
Adhesion of ice in its relation to the de-icing of airplanes

Adhesion of ice in its relation to the de-icing of airplanes

Date: August 1939
Creator: Rothrick, A M & Selden, R
Description: The various possible means of preventing ice adhesion on airplane surfaces are critically reviewed. Results are presented of tests of the adhesives forces between ice and various solid and liquid forces. It is concluded that the de-icing of airplane wings by heat from engine exhaust shows sufficient promise to warrant full-scale tests. For propellers, at least, and possibly for certain small areas such as windshields, radio masts, etc. the use of de-icing or adhesion-preventing liquids will provide the best means of protection.
Contributing Partner: UNT Libraries Government Documents Department
Advantages of oxide films as bases for aluminum pigmented surface coatings for aluminum alloys

Advantages of oxide films as bases for aluminum pigmented surface coatings for aluminum alloys

Date: November 1931
Creator: Buzzard, R W & Mutchler, W H
Description: Both laboratory and weather-exposure corrosion tests showed conclusively that the protection afforded by aluminum pigmented spar varnish coatings applied to previously anodized aluminum surfaces was greatly superior to that afforded by the same coatings applied to surfaces which had simply been cleaned free from grease and not anodized.
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: 1934
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 analysis of the gyroplane rotating-wing system

The aerodynamic analysis of the gyroplane rotating-wing system

Date: March 1934
Creator: Wheatley, John B
Description: An aerodynamic analysis of the gyroplane rotating-wing system is presented herein. This system consists of a freely rotating rotor in which opposite blades are rigidly connected and allowed to rotate or feather freely about their span axis. Equations have been derived for the lift, the lift-drag ratio, the angle of attack, the feathering angles, and the rolling and pitching moments of a gyroplane rotor in terms of its basic parameters. Curves of lift-drag ratio against lift coefficient have been calculated for a typical case, showing the effect of varying the pitch angle, the solidarity, and the average blade-section drag coefficient. The analysis expresses satisfactorily the qualitative relations between the rotor characteristics and the rotor parameters. As disclosed by this investigation, the aerodynamic principles of the gyroplane are sound, and further research on this wing system is justified.
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 4-engine monoplane showing comparison of air-cooled and liquid-cooled engine installations

Aerodynamic characteristics of a 4-engine monoplane showing comparison of air-cooled and liquid-cooled engine installations

Date: July 1939
Creator: Wilson, Herbert A , Jr & Silverstein, Abe
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 4-engine monoplane showing effects of enclosing the engines in the wing and comparisons of tractor- and pusher-propeller arrangements

Aerodynamic characteristics of a 4-engine monoplane showing effects of enclosing the engines in the wing and comparisons of tractor- and pusher-propeller arrangements

Date: April 1938
Creator: Wilson, Herbert A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a large number of airfoils tested in the variable-density wind tunnel

Aerodynamic characteristics of a large number of airfoils tested in the variable-density wind tunnel

Date: 1938
Creator: Pinkerton, Robert M & Greenberg, Harry
Description: The aerodynamic characteristics of a large number of miscellaneous airfoils tested in the variable-density tunnel have been reduced to a comparable form and are published in this report for convenient reference. Plots of the standard characteristics are given in tabular form. Included is a tabulation of important characteristics for the related airfoils reported in NACA report 460. This report, in conjunction with NACA report 610, makes available in comparable and convenient form the aerodynamic data for airfoils tested in the variable-density tunnel since January 1, 1931.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear

The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear

Date: May 1932
Creator: Weick, Fred E & Harris, Thomas E
Description: Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher maximum lift coefficients than conventional trailing-edge flaps, and the lift coefficients were increased still further by moving the axes toward the rear. The highest value of C(sub L max), which was obtained with the largest flap hinged at 90 per cent of the chord from the leading edge, was 2.52 as compared with 1.27 for the basic wing.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of a slotted Clark y wing as affected by the auxiliary airfoil position

The aerodynamic characteristics of a slotted Clark y wing as affected by the auxiliary airfoil position

Date: 1932~
Creator: Wenzinger, Carl J & Shortal, Joseph A
Description: Aerodynamic force tests on a slotted Clark Y wing were conducted in a vertical wind tunnel to determine the best position for a given auxiliary airfoil with respect to the main wing. A systematic series of 100 changes in location of the auxiliary airfoil were made to cover all the probable useful ranges of slot gap, slot width, and slot depth. The results of the investigation may be applied to the design of automatic or controlled slots on wings with geometric characteristics similar to the wing tested. The best positions of the auxiliary airfoil were covered by the range of the tests, and the position for desired aerodynamic characteristics may easily be obtained from charts prepared especially for the purpose.
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
The aerodynamic characteristics of airfoils as affected by surface roughness

The aerodynamic characteristics of airfoils as affected by surface roughness

Date: April 1933
Creator: HOCKER RAY W
Description: The effect on airfoil characteristics of surface roughness of varying degrees and types at different locations on an airfoil was investigated at high values of the Reynolds number in a variable density wind tunnel. Tests were made on a number of National Advisory Committee for Aeronautics (NACA) 0012 airfoil models on which the nature of the surface was varied from a rough to a very smooth finish. The effect on the airfoil characteristics of varying the location of a rough area in the region of the leading edge was also investigated. Airfoils with surfaces simulating lap joints were also tested. Measurable adverse effects were found to be caused by small irregularities in airfoil surfaces which might ordinarily be overlooked. The flow is sensitive to small irregularities of approximately 0.0002c in depth near the leading edge. The tests made on the surfaces simulating lap joints indicated that such surfaces cause small adverse effects. Additional data from earlier tests of another symmetrical airfoil are also included to indicate the variation of the maximum lift coefficient with the Reynolds number for an airfoil with a polished surface and with a very rough one.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of airfoils at negative angles of attack

The aerodynamic characteristics of airfoils at negative angles of attack

Date: 1932~
Creator: Anderson, Raymond F
Description: A number of airfoils, including 14 commonly used airfoils and 10 NACA airfoils, were tested through the negative angle-of-attack range in the NACA variable-density wind tunnel at a Reynolds Number of approximately 3,000,000. The tests were made to supply data to serve as a basis for the structural design of airplanes in the inverted flight condition. In order to make the results immediately available for this purpose they are presented herein in preliminary form, together with results of previous tests of the airfoils at positive angles of attack. An analysis of the results made to find the variation of the ratio of the maximum negative lift coefficient to the maximum positive lift coefficient led to the following conclusions: 1) For airfoils of a given thickness, the ratio -C(sub L max) / +C(sub L max) tends to decrease as the mean camber is increased. 2) For airfoils of a given mean camber, the ratio -C(sub L max) / +C(sub L max) tends to increase as the thickness increases.
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Aerodynamic characteristics of airfoils VI : continuation of reports nos. 93, 124, 182, 244, and 286

Aerodynamic characteristics of airfoils VI : continuation of reports nos. 93, 124, 182, 244, and 286

Date: 1930~
Creator: unknown
Description: This collection of data on airfoils has been made from the published reports of a number of the leading aerodynamic laboratories of this country and Europe. The information which was originally expressed according to the different customs of the several laboratories is here presented in a uniform series of charts and tables suitable for use of designing engineers and for purposes of general reference. The authority for the results here presented is given as the name of the laboratory at which the experiments were conducted, with the size of the model, wind velocity, and year of test.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of anemometer cups

Aerodynamic characteristics of anemometer cups

Date: February 1934
Creator: Brevoort, M J & Joyner, U T
Description: The static lift and drag forces on three hemispherical and two conical cups were measured over a range of angles of attack from 0 degrees to 180 degrees and a range of Reynolds Numbers from very small up to 400,000. The problems of supporting the cup for measurement and the effect of turbulence were also studied. The results were compared with those of other investigators.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of circular-arc airfoils at high speeds

Aerodynamic characteristics of circular-arc airfoils at high speeds

Date: 1932~
Creator: Briggs, L. J. & Dryden, H. L.
Description: The aerodynamic characteristics of eight circular-arc airfoils at speeds of 0.5, 0.8, 0.95, and 1.08 times the speed of sound have been determined in an open-jet air stream 2 inches in diameter, using models of 1-inch chord. The lower surface of each airfoil was plane; the upper surface was cylindrical. As compared with the measurements described in NACA-TR-319, the circular-arc airfoils at speeds of 0.95 and 1.08 times the speed of sound are more efficient than airfoils of the R. A. F. or Clark Y families. At a speed of 0.5 times the speed of sound, the thick circular-arc sections are extremely inefficient, but thin sections compare favorably with those of the R. A. F. family. A moderate round of the sharp edges changes the characteristics very little and is in many instances beneficial. The results indicate that the section of the blades of propellers intended for use at high tip-speeds should be of the circular-arc form for the outer part of the blade and should be changed gradually to the R. A. F. or Clark Y form as the hub is approached.
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The aerodynamic characteristics of eight very thick airfoils from tests in the variable density wind tunnel

The aerodynamic characteristics of eight very thick airfoils from tests in the variable density wind tunnel

Date: 1932~
Creator: Jacobs, Eastman N
Description: Report presents the results of wind tunnel tests on a group of eight very thick airfoils having sections of the same thickness as those used near the roots of tapered airfoils. The tests were made to study certain discontinuities in the characteristic curves that have been obtained from previous tests of these airfoils, and to compare the characteristics of the different sections at values of the Reynolds number comparable with those attained in flight. The discontinuities were found to disappear as the Reynolds number was increased. The results obtained from the large-scale airfoil, a symmetrical airfoil having a thickness ratio of 21 per cent, has the best general characteristics.
Contributing Partner: UNT Libraries Government Documents Department