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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1937
 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 1, 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
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: January 1, 1937
Creator: Platt, Robert C
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 flow around finned cylinders

Air flow around finned cylinders

Date: January 1, 1937
Creator: Brevoort, M J
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.
Contributing Partner: UNT Libraries Government Documents Department
Air flow in the boundary layer near a plate

Air flow in the boundary layer near a plate

Date: January 1, 1937
Creator: Dryden, Hugh L
Description: The published data on the distribution of speed near a thin flat plate with sharp leading edge placed parallel to the flow (skin friction plate) are reviewed and the results of some additional measurements are described. The purpose of the experiments was to study the basic phenomena of boundary-layer flow under simple conditions.
Contributing Partner: UNT Libraries Government Documents Department
Air propellers in yaw

Air propellers in yaw

Date: January 1, 1937
Creator: Lesley, E P
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.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
Aircraft compass characteristics

Aircraft compass characteristics

Date: January 1, 1937
Creator: Peterson, John B
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.
Contributing Partner: UNT Libraries Government Documents Department
Airfoil section characteristics as affected by variations of the Reynolds number

Airfoil section characteristics as affected by variations of the Reynolds number

Date: January 1, 1937
Creator: Jacobs, Eastman N
Description: Report presents the results of an investigation of a systematically chosen representative group of related airfoils conducted in the NACA variable-density wind tunnel over a wide range of Reynolds number extending well into the flight range. The tests were made to provide information from which the variations of airfoil section characteristics with changes in the Reynolds number could be inferred and methods of allowing for these variations in practice could be determined. This work is one phase of an extensive and general airfoil investigation being conducted in the variable-density tunnel and extends the previously published researches concerning airfoil characteristics as affected by variations in airfoil profile determined at a single value of the Reynolds number.
Contributing Partner: UNT Libraries Government Documents Department
The airspeed "Oxford" training airplane (British) : a two-engine cantilever monoplane

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

Date: September 1, 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: January 1, 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
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