UNT Libraries Government Documents Department - 22 Matching Results

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The cross-flow plate-type intercooler

Description: Report presenting a mathematical analysis of plate-type intercooler design for both turbulent and laminar flow. Charts are presented to show how the plate-type intercooler volume, weight, plate area, frontal area, and linear dimensions can be varied without changing the intercooler operating conditions. An experimental investigation was also carried out with a plate-type intercooler unit to check the validity of the heat-transfer and pressure-drop theories for the airflow between very closely spaced plates.
Date: April 1942
Creator: Pinkel, Benjamin; Reuter, J. George & Valerino, Michael F.

Flight investigation of the performance and cooling characteristics of a long-nose high-inlet-velocity cowling on the XP-42 airplane

Description: Report presenting the results of a series of flight tests of the maximum speed and cooling characteristics in high-speed level flight and in climb of the XP-42 airplane equipped with a long-nose high-inlet-velocity cowling. The results indicated that a maximum speed of 338 miles per hour at 870 horsepower at 17,000 feet was achievable, which is above the engine critical altitude. Pressure measurements in the entrances in the cylinder baffles showed a uniform distribution of pressure on the front of the engine in high-speed level flight and a fairly uniform distribution in full-power climb.
Date: April 1942
Creator: Bailey, F. J., Jr.; Johnston, J. Ford & Voglewede, T. J.

Generalized equations for selection charts for heat exchangers in aircraft

Description: "The equations that describe the operation of a heat exchanger - the equations for pressure drop, rate of heat transfer, and power expenditure - have been put into nondimensional, generalized form. These generalized equations can be used for constructing selection charts for various types of aircraft heat exchangers. Such charts would facilitate choice of heat-exchanger dimensions for any given set of operating conditions. A typical selection chart is presented" (p. 1).
Date: April 1942
Creator: Tifford, Arthur N. & Wood, George P.

Investigation of flow through an intercooler set at various angles to the supply duct

Description: Report presenting an investigation to determine the flow losses that occur as a result of locating the axis of an intercooler at various angles with respect to the supply-duct axis and also to determine the flow pattern throughout the intercooler. The flow losses were found to be small for angles of inclination up to about 70 degrees. The distribution of flow through the intercooler also appeared to be fairly uniform up to about this angle.
Date: April 1942
Creator: Nichols, Mark R.

Measurements of the Flying Qualities of a Hawker Hurricane Airplane

Description: Report presenting an investigation of the flying qualities of a Hawker Hurricane airplane. Thirteen flights and approximately 17 hours of flying time were required to complete the tests, which included extensive measurements of stability, controllability, and stalling characteristics. The results were similar to the flying qualities of other previously studied pursuit airplanes.
Date: April 1942
Creator: Nissen, J. M. & Phillips, W. H.

A Method of Shear-Lag Analysis of Box Beams for Axial Stresses, Shear Stresses, and Shear Center

Description: Report presenting a practical and relatively rapid method of compensating for shear lag in box-beam analysis with accuracy sufficient for design purposes. Effectiveness curves for box beam elements are derived for an ideal, symmetrical structure. Tabular computation forms for rapid, accurate calculations of axial stresses, shear center, and shear stresses for beam with shear lag are induced.
Date: April 1942
Creator: Erlandsen, Oscar, Jr. & Mead, Lawrence M., Jr.

Newsmap. Monday, April 27, 1942 : week of April 17 to 24

Description: Text describes action on various war fronts. Includes photographs: Lieut. Bulkeley -- Nip Nipper de luxe, Lieut. Comm. Edward H. O'Hare -- Brewster "Buffalo" -- The guns were going on -- The big Wellingtons did not rest -- Training of airborne Infantry. Large world map is keyed to text: Japs confused on raid -- Chinese rescue British -- Corregidor holds -- Timor fight still on -- blame set for fire -- President honors flyer -- Gen. Marshall returns -- strike idleness small -- manpower mobilization -- Brewster plant seized -- Argentine ship hit -- radio detectors used -- "Peace Offensive" due-- Lubeck laid low-- commandos raid again -- Reds close for action -- Malta takes high toll -- Laval favors Nazis. Inset maps: Honshu, Japan ; western Europe. Also includes 2 pictographs: Happy Birthday, Dear Adolf; Telefact: materials for victory.
Date: April 27, 1942
Creator: [United States]. Army Orientation Course.

Pressure distribution on wings in reversed flow

Description: The series of pressure distribution measurements at three test sections on NACA airfoils 2212 and M6 within 170 to 210 angles of attack in reversed flow proved to be largely independent of the profile form. In contradiction to the pressure distribution in normal flow considerable negative pressure from the upper surface spills over onto the lower surface, and vice versa, even in the zone of sound flow. The results are presented as chord-wise pressure and load distribution. The spanwise lift distribution and the total lift coefficients of the wing obtained by integration manifest approximate agreement with the behavior of a diagonally disposed flat plate. By consideration of the ground effect (represented by a flat wall) the lower surface of the wing shows an increase in the low pressure.
Date: April 1, 1942
Creator: Naumann, A.

Recent results in rocket flight technique

Description: The concept of the effective ejection velocity of a rocket engine is explained and the magnitude of the attainable ejection velocity theoretically and experimentally investigated. Velocities above 3000 meters per second (6700 mph) are actually measured and the possibilities of further increases shown.
Date: April 1, 1942
Creator: Sanger, Eugen

Theoretical solution of profile drag

Description: After a survey of the customary procedures for appraising the profile drag in which pressure drag was discounted and the methods for computing the laminar and turbulent friction flow, the author proposes a method by which the pressure drag can be computed with the aid of the displacement thickness of the frictional layer. The method is restricted to the case where the effects, caused by separation of frictional layer, are small. Then the total profile drag can be expressed solely by quantities derived from the velocity distribution in the frictional layer immediately at the trailing edge.
Date: April 1942
Creator: Pretsch, J.