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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1937
 Collection: National Advisory Committee for Aeronautics Collection
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.
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Aerodynamic characteristics of NACA 23012 and 23021 airfoils with 20-percent-chord external-airfoil flaps of NACA 23012 section

Aerodynamic characteristics of NACA 23012 and 23021 airfoils with 20-percent-chord external-airfoil flaps of NACA 23012 section

Date: 1937~
Creator: Platt, Robert C & Abbott, Ira H
Description: Report presents the results of an investigation of the general aerodynamic characteristics of the NACA 23012 and 23021 airfoils, each equipped with a 0.20c external flap of NACA 23012 section. The tests were made in the NACA 7 by 10-foot and variable-density wind tunnels and covered a range of Reynolds numbers that included values corresponding to those for landing conditions of a wide range of airplanes. Besides a determination of the variation of lift and drag characteristics with position of the flap relative to the main airfoil, complete aerodynamic characteristics of the airfoil-flap combination with a flap hinge axis selected to give small hinge moments were measured in the two tunnels. Some measurements of air loads on the flap itself in the presence of the wing were made in the 7 by 10-foot wind tunnel.
Contributing Partner: UNT Libraries Government Documents Department
Air propellers in yaw

Air propellers in yaw

Date: January 1, 1937
Creator: Lesley, E P; Worley, George F & Moy, Stanley
Description: Report presents the results of tests conducted at Stanford University of a 3-foot model propeller at four pitch settings and at 0 degree, 10 degrees, 20 degrees, and 30 degrees yaw. In addition to the usual propeller coefficients, cross-wind and vertical forces and yawing, pitching, and rolling moments were determined about axes having their origin at the intersection of the blade axis and the axis of rotation. The tests showed that the maximum efficiency was reduced only slightly for angles of yaw up to 10 degrees but that at 30 degrees yaw the loss in efficiency was about 10 percent. In all cases the cross-wind force was found to be greater than the cross-wind component of the axial thrust. With a yawed propeller an appreciable thrust was found for v/nd for zero thrust at zero yaw. Yawing a propeller was found to induce a pitching moment that increased in magnitude with yaw.
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Aircraft accidents.method of analysis

Aircraft accidents.method of analysis

Date: January 1, 1937
Creator: unknown
Description: This report is a revision of NACA-TR-357. It was prepared by the Committee on Aircraft Accidents. The purpose of this report is to provide a basis for the classification and comparison of aircraft accidents, both civil and military.
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Aircraft compass characteristics

Aircraft compass characteristics

Date: January 1, 1937
Creator: Peterson, John B. & Smith, Clyde W.
Description: A description of the test methods used at the National Bureau of Standards for determining the characteristics of aircraft compasses is given. The methods described are particularly applicable to compasses in which mineral oil is used as the damping liquid. Data on the viscosity and density of certain mineral oils used in United States Navy aircraft compasses are presented. Characteristics of Navy aircraft compasses IV to IX and some other compasses are shown for the range of temperatures experienced in flight. Results of flight tests are presented. These results indicate that the characteristic most desired in a steering compass is a short period and, in a check compass, a low overswing.
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The airspeed "Oxford" training airplane (British) : a two-engine cantilever monoplane

The airspeed "Oxford" training airplane (British) : a two-engine cantilever monoplane

Date: September 1937
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Alternating-current equipment for the measurement of fluctuations of air speed in turbulent flow

Alternating-current equipment for the measurement of fluctuations of air speed in turbulent flow

Date: March 1937
Creator: Mock, W. C., Jr.
Description: Recent electrical and mechanical improvements have been made in the equipment developed at the National Bureau of Standards for measurement of fluctuations of air speed in turbulent flow. Data useful in the design of similar equipment are presented. The design of rectified alternating-current power supplies for such apparatus is treated briefly, and the effect of the power supplies on the performance of the equipment is discussed.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of lateral stability in power-off flight with charts for use in design

An analysis of lateral stability in power-off flight with charts for use in design

Date: January 1, 1937
Creator: Zimmerman, Charles H
Description: The aerodynamic and mass factors governing lateral stability are discussed and formulas are given for their estimation. Relatively simple relationships between the governing factors and the resulting stability characteristics are presented. A series of charts is included with which approximate stability characteristics may be rapidly estimated. The effects of the various governing factors upon the stability characteristics are discussed in detail. It is pointed out that much additional research is necessary both to correlate stability characteristics with riding, flying, and handling qualities and to provide suitable data for accurate estimates of those characteristics of an airplane while it is in the design stage.
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An analysis of the factors that determine the periodic twist of an autogiro rotor blade, with a comparison of predicted and measured results

An analysis of the factors that determine the periodic twist of an autogiro rotor blade, with a comparison of predicted and measured results

Date: April 14, 1937
Creator: Wheatley, John B
Description: Report presents an analysis of the factors that determine the periodic twist of a rotor blade under the action of the air forces on it. The results of the analysis show that the Fourier coefficients of the twist are linear expressions involving only the tip-speed ratio, the pitch setting, the inflow coefficient, the pitching-moment coefficient of the blade airfoil section, and the physical characteristics of the rotor blade and machine. The validity of the analysis was examined by using it to predict the twist of a rotor whose twist characteristics had previously been measured in flight. The agreement between the calculated and experimental results was satisfactory.
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An analytical and experimental study of the effect of periodic blade twist on the thrust, torque, and flapping motion of an autogiro rotor

An analytical and experimental study of the effect of periodic blade twist on the thrust, torque, and flapping motion of an autogiro rotor

Date: 1937
Creator: Wheatley, John B
Description: An analysis is made of the influence on autogiro rotor characteristics of a periodic blade twist that varies with the azimuth position of the rotor blade and the results are compared with experimental data. The analysis expresses the influence of this type of twist upon the thrust, torque, and flapping motion of the rotor. The check against experimental data shows that the periodic twist has a pronounced influence on the flapping motion and that this influence is accurately predicted by the analysis. The influence of the twist upon the thrust and torque could be demonstrated only indirectly, but its importance is indicated.
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (22nd).administrative report including Technical Report nos. 542 to 576

Annual report of the National Advisory Committee for Aeronautics (22nd).administrative report including Technical Report nos. 542 to 576

Date: 1937
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
The apparent width of the plate in compression

The apparent width of the plate in compression

Date: July 1, 1937
Creator: Marguerre, Karl
Description: The following investigation treats the load capacity of a rectangular plate stressed in compression on one direction (x) beyond the buckling limit. The plate is rotatable (i.e., free from moments) supported at all four sides by bending-resistant beams.
Contributing Partner: UNT Libraries Government Documents Department
Armstrong Whitworth 27 "Ensign" commercial airplane (British) : an all-metal high-wing monoplane

Armstrong Whitworth 27 "Ensign" commercial airplane (British) : an all-metal high-wing monoplane

Date: May 1, 1937
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Auto-ignition and combustion of diesel fuel in a constant-volume bomb

Auto-ignition and combustion of diesel fuel in a constant-volume bomb

Date: October 5, 1937
Creator: Selden, Robert F
Description: Report presents the results of a study of variations in ignition lag and combustion associated with changes in air temperature and density for a diesel fuel in a constant-volume bomb. The test results have been discussed in terms of engine performance wherever comparisons could be drawn. The most important conclusions drawn from this investigation are: the ignition lag was essentially independent of the injected fuel quantity. Extrapolation of the curves for the fuel used shows that the lag could not be greatly decreased by exceeding the compression-ignition engines. In order to obtain the best combustion and thermal efficiency, it was desirable to use the longest ignition lag consistent with a permissible rate of pressure rise.
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Baynes Bee light airplane (British) : a two-seat high-wing monoplane

Baynes Bee light airplane (British) : a two-seat high-wing monoplane

Date: June 1, 1937
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The behavior of thin-will monocoque cylinders under torsional vibration

The behavior of thin-will monocoque cylinders under torsional vibration

Date: August 1, 1937
Creator: Pekelsma, Robert E
Description: Curves of forced frequency against amplitude are presented for the conditions where the forced frequency is both increased and decreased into the resonant range. On the basis of these curves it is shown that the practical resonance frequency is the point where wrinkling first occurs and that the resonance frequency will be subject to considerable travel once permanent wrinkles appear in the vibrating shell. The decreasing mode of striking resonance is found to be by far the most destructive condition.
Contributing Partner: UNT Libraries Government Documents Department
Bending tests of circular cylinders of corrugated aluminum-alloy sheet

Bending tests of circular cylinders of corrugated aluminum-alloy sheet

Date: March 1, 1937
Creator: Buckwalter, John C; Reed, Warren D & Niles, Alfred S
Description: Bending tests were made of two circular cylinders of corrugated aluminum-alloy sheet. In each test failure occurred by bending of the corrugations in a plane normal to the skin. It was found, after analysis of the effect of short end bays, that the computed stress on the extreme fiber of a corrugated cylinder is in excess of that for a flat panel of the same basic pattern and panel length tested as a pin-ended column. It is concluded that this increased strength was due to the effects of curvature of the pitch line. It is also concluded from the tests that light bulkheads closely spaced strengthen corrugated cylinders very materially.
Contributing Partner: UNT Libraries Government Documents Department
Blower cooling of finned cylinders

Blower cooling of finned cylinders

Date: January 1, 1937
Creator: Schey, Oscar W & Ellerbrock, Herman H , Jr
Description: Several electrically heated finned steel cylinders enclosed in jackets were cooled by air from a blower. The effect of the air conditions and fin dimensions on the average surface heat-transfer coefficient q and the power required to force the air around the cylinders were determined. Tests were conducted at air velocities between the fins from 10 to 130 miles per hour and at specific weights of the air varying from 0.046 to 0.074 pound per cubic foot. The fin dimensions of the cylinders covered a range in pitches from 0.057 to 0.25 inch average fin thicknesses from 0.035 to 0.04 inch, and fin widths from 0.67 to 1.22 inches.
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Calculated and measured pressure distributions over the midspan section of the NACA 4412 airfoil

Calculated and measured pressure distributions over the midspan section of the NACA 4412 airfoil

Date: January 1, 1937
Creator: Pinkerton, Robert M
Description: Pressures were simultaneously measured in the variable-density tunnel at 54 orifices distributed over the midspan section of 5 by 30 inch rectangular model of the NACA 4412 airfoil at 17 angles of attack ranging from -20 degrees to 30 degrees at a Reynolds number of approximately 3,000,000. Accurate data were thus obtained for studying the deviations of the results of potential-flow theory from measured results. The results of the analysis and a discussion of the experimental technique are presented.
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Characteristics of six propellers including the high-speed range

Characteristics of six propellers including the high-speed range

Date: January 1, 1937
Creator: Theodorsen, Theodore; Stickle, George W & Brevoort, M J
Description: This investigation is part of an extensive experimental study that has been carried out at full scale in the NACA 20-foot tunnel, the purpose of which has been to furnish information in regard to the functioning of the propeller-cowling-nacelle unit under all conditions of take-off, climbing, and normal flight. This report presents the results of tests of six propellers in the normal and high-speed flight range and also includes a study of the take-off characteristics.
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Charts expressing the time, velocity, and altitude relations for an airplane diving in a standard atmosphere

Charts expressing the time, velocity, and altitude relations for an airplane diving in a standard atmosphere

Date: April 1, 1937
Creator: Pearson, H A
Description: In this report charts are given showing the relation between time, velocities, and altitude for airplanes having various terminal velocities diving in a standard atmosphere. The range of starting altitudes is from 8,000 to 32,000 feet, and the terminal velocities vary from 150 to 550 miles per hour. A comparison is made between an experimental case and the results obtained from the charts. Examples pointing out the use of the charts are included.
Contributing Partner: UNT Libraries Government Documents Department
Charts for checking the stability of plane systems of rods

Charts for checking the stability of plane systems of rods

Date: September 1, 1937
Creator: Borkmann, K
Description: Charts are presented for checking the stability of plane systems of rods, the use of the charts being illustrated by examples. It is also indicated how best to combine the individual members to form stable structures.
Contributing Partner: UNT Libraries Government Documents Department
Compression-ignition engine performance at altitudes and at various air pressures and temperatures

Compression-ignition engine performance at altitudes and at various air pressures and temperatures

Date: November 1, 1937
Creator: Moore, Charles S & Collins, John H
Description: Engine test results are presented for simulated altitude conditions. A displaced-piston combustion chamber on a 5- by 7-inch single cylinder compression-ignition engine operating at 2,000 r.p.m. was used. Inlet air temperature equivalent to standard altitudes up to 14,000 feet were obtained. Comparison between performance at altitude of the unsupercharged compression-ignition engine compared favorably with the carburetor engine. Analysis of the results for which the inlet air temperature, inlet air pressure, and inlet and exhaust pressure were varied indicates that engine performance cannot be reliably corrected on the basis of inlet air density or weight of air charge. Engine power increases with inlet air pressure and decreases with inlet air temperatures very nearly as straight line relations over a wide range of air-fuel ratios. Correction factors are given.
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Considerations affecting the additional weight required in mass balance of ailerons

Considerations affecting the additional weight required in mass balance of ailerons

Date: August 1, 1937
Creator: Diehl, W S
Description: This paper is essentially a consideration of mass balance of ailerons from a preliminary design standpoint, in which the extra weight of the mass counterbalance is the most important phase of the problem. Equations are developed for the required balance weight for a simple aileron and this weight is correlated with the mass-balance coefficient. It is concluded the location of the c.g. of the basic aileron is of paramount importance and that complete mass balance imposes no great weight penalty if the aileron is designed to have its c.g. inherently near to the hinge axis.
Contributing Partner: UNT Libraries Government Documents Department
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