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UNT Libraries Government Documents Department
Resource Type:
Report
Decade:
1930-1939
Year:
1937
Month:
November
Compression-ignition engine performance at altitudes and at various air pressures and temperatures
Date: November 1, 1937
Creator: Moore, Charles S
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.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc54355/
Flight tests of an airplane showing dependence of the maximum lift coefficient on the test conditions
Date: November 1, 1937
Creator: Soule, H A
Description: Data are presented to show the extent to which the maximum lift coefficient and consequently the minimum speed of an airplane, determined by flight tests, may vary with test conditions. The data show that cl-max may vary as much as 14 percent, depending on the altitude and wing loading at which the tests were made, the position or motion of the propeller, and the rate at which the angle of attack is changing when the maximum lift coefficient is obtained. The variation of the maximum lift coefficient with these factors, which are under the control of the test engineer, shows the need of standardizing the test procedure. A further variation is shown with wing conditions as affected by weathering and vibration, factors that cannot be completely controlled.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc54381/
Maximum forces applied by pilots to wheel-type controls
Date: November 1, 1937
Creator: Mcavoy, William H
Description: Measurements were made of the maximum push, pull, and tangential forces that could be applied to airplane wheel-type controls for a wide range of fore-and-aft positions of the wheel. The measurements were conducted with several sizes of wheels and several heights of the center of the wheel above the seat. Various one and two-hand grips with pilots both secure and free were studied for each of the two pilots used in the investigation.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc54387/
Performance characteristics of venturi tubes used in aircraft for operating air-driven gyroscopic instruments
Date: November 1, 1937
Creator: Sontag, Harcourt
Description: Wind tunnel and flight tests were made to determine the performance characteristics of two designs of commercially available venturi tubes used in airplanes to operate air-driven gyroscopic instruments. Data obtained at sea level may be used to make approximate predictions of performance at higher altitudes. There is some indication that this may also be done for single venturi tubes. For a given installation in which an air-driven instrument is connected through tubing with a venturi tube, the volume rate of induced air flow is approximately proportional to the product of indicated air speed and the square root of the ratio of standard to ambient air pressure. The efficiency of such a system at a given altitude is constant. Rather large variations in suction and efficiency were found for individual tubes of the same design. Cylindrical fairings on the external surface resulted in a reduction of both drag and suction but little change in efficiency.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc54389/
Pressure drop across finned cylinders enclosed in a jacket
Date: November 1, 1937
Creator: Rollin, Vern G
Description: The pressure drop across finned cylinders in a jacket for a range of air speeds from approximately 13 to 230 miles per hour has been investigated. Tests were made to determine the effect on the pressure drop of changes in fin space, fin width, jacket entrance and exit areas, skirt-approach radius, and the use of fillets and a separator plate at the rear of the cylinder. The pressure drop across the cylinder increased as the fin space decreased, the increase being very rapid at fin spaces smaller than approximately 0.20 inch. Fin width had little effect on the pressure drop for the range of widths tested. The pressure drop across the cylinder was nearly halved by increasing the skirt-approach radius from 3/4 inch to 1-1/4 inches, but fillets and a separator plate at the rear of the cylinder had little effect on the pressure drop. The pressure drop across a cylinder with tapered fins was greater than that for a cylinder having rectangular fins with the same effective fin spacing.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc54370/
Synthetic resins in aircraft construction - their composition, properties, present state of development and application to light structures
Date: November 1, 1937
Creator: Riechers, K
Description: This report gives a brief review of the properties that have been attained with the synthetic materials with which we are at present familiar. Results of investigations are presented as well as possibilities for construction applications. Endurance strength and bonding tests are also presented.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc63349/
Tapered wings, tip stalling, and preliminary results from tests of the stall-control flap
Date: November 1, 1937
Creator: Jacobs, Eastman N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61414/
Universal logarithmic law of velocity distribution as applied to the investigation of boundary layer and drag of streamline bodies at large Reynolds number
Date: November 1, 1937
Creator: Gurjienko, G
Description: In the present paper we shall consider a figure of revolution, so that the formulas applicable to the more simple cases as, for example, a wing or flat plate will follow from our equations as corollaries. For checking the results of our theory, we made use of the data derived from the tests of Freeman on a 1/40-scale model of the airship "Akron" conducted in the large NACA wind tunnel. In the first part we shall derive the fundamental equation for a body of revolution according to the Karman theory in its original form, and in the second part we shall give all the comparisons of the results of tests with the modified theory.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc63346/