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An investigation of aircraft heaters 13: performance of corrugated and noncorrugated fluted type exhaust gas-air heat exchangers

Description: Report presenting thermal and static pressure-drop performance data on three fluted-type heat exchangers. Two of the heaters used corrugated surfaces along the fluid passages and the third one was constructed with non-corrugated surfaces. Results regarding a comparison of results on the noncorrugated heater using two different air shrouds, heat transfer, isothermal static pressure drop, nonisothermal static pressure drop, and heater surface temperatures are provided.
Date: August 1943
Creator: Boelter, L. M. K.; Guibert, A. G.; Miller, M. A. & Morrin, E. H.
Partner: UNT Libraries Government Documents Department

An investigation of aircraft heaters 10: measured and predicted performance of a fluted-type exhaust gas and air heat exchanger

Description: Report presenting performance data on a small exhaust gas and air heat exchanger. The heat transfer rates were measured using about 8000 pounds per hour of exhaust gas and 4300 pounds per hour of ventilating air. The thermal performance of heater no. 2 can be estimated to 3 to 17 percent by use of the method described in the report.
Date: March 1943
Creator: Boelter, L. M. K.; Dennison, H. G.; Guibert, A. G. & Morrin, E. H.
Partner: UNT Libraries Government Documents Department

An investigation of aircraft heaters 11: measured and predicted performance of a slotted-fin exhaust gas and air heat exchanger

Description: Report presenting the thermal and pressure drop performance data of a slotted-fin Stewart-Warner exhaust gas and ventilating air heat exchanger. Three different crossflow air shrouds were used in testing. The rate of heat transfer was about the same for each shroud, but the static pressure drops varied greatly.
Date: April 1943
Creator: Boelter, L. M. K.; Miller, M. A.; Sharp, W. H. & Morrin, E. H.
Partner: UNT Libraries Government Documents Department

Correlation of single-cylinder cooling tests of a Pratt and Whitney R-2800-21 engine cylinder with wind-tunnel tests of a Pratt and Whitney R-2800-27 engine

Description: Report presenting an equation in which it is possible to correlate the cooling characteristics of an engine. Results regarding engine cooling, engine performance, and estimated cooling-pressure-drop requirements are provided.
Date: December 1943
Creator: Ellerbrock, Herman H., Jr.
Partner: UNT Libraries Government Documents Department

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane 3: low-inlet-velocity cowling without fan or propeller cuffs, with axial-flow fan alone, and with two different sets of propeller cuffs

Description: Report presenting the results of flight measurements of performance and cooling characteristics of the XP-42 airplane equipped with a short-nose low-inlet-velocity cowling. Testing included measurements in level flight and climb of the effects of a spinner-mounted axial-flow fan without propeller cuffs, no fan or cuffs, and two different sets of propeller cuffs.
Date: January 1943
Creator: Johnston, J. Ford & Voglewede, T. J.
Partner: UNT Libraries Government Documents Department

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane 2: low-inlet-velocity cowling with axial-flow fan and propeller cuffs

Description: Report presenting results from a series of flight tests of the performance and cooling characteristics in high-speed level flight and in climb of the XP-42 airplane equipped with a short-nose low-inlet-velocity cowling and an axial-flow fan mounted on the spinner. Results regarding maximum speed and pressures and temperatures are provided.
Date: January 1943
Creator: Johnston, J. Ford & Voglewede, T. J.
Partner: UNT Libraries Government Documents Department

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane 4: high-inlet-velocity cowling tested in climb with and without propeller cuffs and in high-speed level flight without propeller cuffs

Description: Report presenting flight measurements of the performance and cooling characteristics of a short-nose high-inlet-velocity cowling on the XP-42 for conditions of climb with and without propeller cuffs and for high speed without cuffs. The speed of the airplane was approximately 1 mile per hour greater without propeller cuffs than the previously measured value with cuffs. Results regarding maximum speed, pressures and temperatures, and ground cooling are provided.
Date: January 1943
Creator: Johnston, J. Ford & Voglewede, T. J.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Calculations of the Performance of a Compression-Ignition Engine-Compressor Turbine Combination 1: Performance of a Highly Supercharged Compression-Ignition Engine

Description: From Summary: "Small high-speed single-cylinder compression-ignition engines were tested to determine their performance characteristics under high supercharging. Calculations were made on the energy available in the exhaust gas of the compression-ignition engines. The maximum power at any given maximum cylinder pressure was obtained when the compression pressure was equal to the maximum cylinder pressure. Constant-pressure combustion was found possible at an engine speed of 2200 rpm."
Date: December 1945
Creator: Sanders, J. C. & Mendelson, Alexander
Partner: UNT Libraries Government Documents Department

Correlation of exhaust-valve temperatures with engine operating conditions and valve design

Description: Report presenting a theory regarding engine-cooling variables from a previous report, which was used as a basis for the development of a semi-empirical equation to correlate exhaust-valve temperature with engine conditions. Results regarding the determination of constants, influences of operating variables on mean effective gas temperatures, thermal-resistance factor, and accuracy of correlating equation are provided.
Date: October 1945
Creator: Zipkin, M. A. & Sanders, J. C.
Partner: UNT Libraries Government Documents Department

Flight tests of several exhaust-gas-to-air heat exchangers

Description: Report presenting an investigation of thirteen exhaust-gas-to-air heat exchangers to determine the practicability of the use of such heat exchangers in the thermal ice-prevention systems on aircraft. The results show that the exchangers constitute an excellent source of heated air for aircraft ice prevention and can be constructed to resist thermal and vibrational stresses.
Date: March 1944
Creator: Jackson, Richard & Hillendahl, Wesley H.
Partner: UNT Libraries Government Documents Department

A comparison of analytically and experimentally determined isothermal pressure losses in a heat-exchanger installation

Description: The results of this analysis indicate that isothermal pressure losses can be predicted analytically in the type of ducting system which may be broken down into the elementary forms of elbows, diffusers, and straight ducts for which pressure-loss data are published.
Date: May 1945
Creator: Hillendahl, Wesley H.
Partner: UNT Libraries Government Documents Department

Analysis of a thermal ice-prevention system for wing leading-edge landing-light installations

Description: From Introduction: "A typical ice formation on a wing leading-edge-type light installation is shown in figure 1. Although the primary purpose of this analytic investigation was to determine the practicability of providing a landing-light thermal ice-prevention system which could be incorporated with the wing leading-edge thermal ice-prevention system of the B-17 F airplane, the analysis has been developed in a general form for future application to similar deigns. "
Date: January 1944
Creator: Hillendahl, Wesley H.
Partner: UNT Libraries Government Documents Department

Improved baffle designs for air-cooled engine cylinders

Description: Report presenting an investigation to determine methods for improving the cooling of air-cooled engine cylinders by means of baffle modifications. Testing was conducted using a Pratt & Whitney R-1830-43 engine mounted on a ground test stand. Results regarding temperature data for variations in atmospheric conditions, temperature measurements at various points along the cylinder, and some of the implied effects of baffle modifications are provided.
Date: August 1943
Creator: Kinghorn, George F.
Partner: UNT Libraries Government Documents Department

The longitudinal stability of flying boats as determined by tests of models in the NACA tank 1: methods used for the investigation of longitudinal stability characteristics

Description: Report presenting testing of dynamic models that has been helpful in the determination of the longitudinal stability characteristics on the water of a number of specific flying boats. Results regarding the constant-speed tests, accelerated runs, effect of variations in moment of inertia, effect of variations in mass moving vertically, effect of variations of depth of step, and effect of variations of gross load coefficient are provided.
Date: November 1942
Creator: Olson, Roland E. & Land, Norman S.
Partner: UNT Libraries Government Documents Department

Effect of several methods of increasing knock-limited power on cylinder temperatures

Description: Report presenting a study to determine the effect of several methods of increasing the knock-limited power on critical cylinder temperatures. The knock-limited indicated horsepower and cylinder temperatures were determined for a Wright R-2600-8 cylinder under specified operating conditions. The most satisfactory method of increasing knock limited power was found to be internal cooling with water and the least satisfacotry was increasing the engine speed.
Date: September 1944
Creator: Cook, Harvey A.; Vandeman, Jack E. & Brown, Kenneth D.
Partner: UNT Libraries Government Documents Department

The effect of spanwise mass distribution upon the spin characteristics of airplanes as determined by model tests conducted in the free-spinning wind tunnel

Description: Report presenting an investigation to determine whether the difference in the spanwise loading of the two types of aircraft were responsible for the differences in spin characteristics, particularly in regards to angle of attack.
Date: August 1942
Creator: Kamm, Robert W.
Partner: UNT Libraries Government Documents Department

Column and plate compressive strengths of aircraft structural materials: 17S-T aluminum-alloy sheet

Description: From Summary: "Column and plate compressive strengths of 17S-T aluminum-alloy sheet were determined both within and beyond the elastic range from tests of thin-strip columns and from local-instability tests of formed Z- and channel-section columns. These tests are part of an extensive research investigation to provide data on the structural strengths of various aircraft materials. Results are presented in the form of curves and charts that may be used in the design and analysis of aircraft structures."
Date: June 1945
Creator: Heimerl, George J. & Roy, J. Albert
Partner: UNT Libraries Government Documents Department

Column and plate compressive strengths of aircraft structural materials: extruded 75S-T aluminum alloy

Description: Report presenting column and plate compressive strengths of extruded 75S-T aluminum alloy both within and beyond the elastic range from tests of thin-strip columns and local-instability tests of H-, Z-, and channel-section columns. The tests are part of an extensive research investigation to provide data on the structural strength of various aircraft materials. Results regarding compressive stress-strain curves and column and plate compressive strengths are provided.
Date: July 1945
Creator: Heimerl, George J. & Roy, J. Albert
Partner: UNT Libraries Government Documents Department

Column and plate compressive strengths of aircraft structural materials: extruded 24S-T aluminum alloy

Description: Report presenting column and plate compressive strengths of extruded 24S-T aluminum alloy determined both within and beyond the elastic range from tests of thin-strip columns and local-instability tests of H-, Z-, and channel-section columns. The tests are part of a research investigation to provide data on the structural strength of various aircraft materials. Results regarding compressive stress-strain curves and column and plate compressive strengths are provided.
Date: July 1945
Creator: Heimerl, George J. & Roy, J. Albert
Partner: UNT Libraries Government Documents Department

Effect of an aromatic mixture added to two 100-octane fuels on engine temperatures and fuel consumption

Description: Report presenting tests conducted with an air-cooled cylinder on two fuels rated at approximately 100-octane number by the C.F.R. aviation method with and without a 40-percent addition of an aromatic mixture. The aromatic mixture consisted of 50 percent toluene, 37.5 percent xylene, and 12.5 percent benzene. Results regarding engine performance and engine temperature are provided.
Date: June 1942
Creator: Krsek, Alois, Jr. & Jones, Anthony W.
Partner: UNT Libraries Government Documents Department

The effect of pitch on force and moment characteristics of full-scale propellers of five solidities

Description: Report presenting an investigation in the 20-foot propeller-research tunnel to determine the effect of variations in angle of pitch on the aerodynamic characteristics of several propeller combinations. The combinations investigated included two-, three-, four-, and six-blade single-rotating propellers and a six-blade dual-rotating propeller on a nacelle with four angles of thrust axis. The propulsive efficiency was found to decrease as the angle of pitch increased.
Date: June 1942
Creator: Runckel, Jack F.
Partner: UNT Libraries Government Documents Department

Application of a numerical procedure to stress analysis of stringer-reinforced panels

Description: From Introduction: "In the present paper a numerical procedure for the stress analysis of flat-sheet and stringer combinations of arbitrary construction and loading is presented and applied to axially loaded panels and to the reinforced covers of box beams."
Date: March 1945
Creator: Kempner, Joseph
Partner: UNT Libraries Government Documents Department