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  • Chemistry  (31,870)
  • Aircraft Propulsion and Power
  • Engineering
  • 1970-1974  (27,658)
  • 1940-1944  (4,721)
Collection
Keywords
Publisher
Years
Year
  • 1
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    Compressibility and Heating Effects on Pressure Loss and Cooling of a Baffled Cylinder Barrel (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Theoretical investigations have shown that, because air is compressible, the pressure-drop requirements for cooling an air-cooled engine will be much greater at high altitudes and high speeds than at sea level and low speeds. Tests were conducted by the NACA to obtain some experimental confirmation of the effect of air compressibility on cooling and pressure loss of a baffled cylinder barrel and to evaluate various methods of analysis. The results reported in the present paper are regarded as preliminary to tests on single-cylinder and multi-cylinder engines. Tests were conducted over a wide range of air flows and density altitudes.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-783
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Hypersonic Research Facilities Study - Volume IV, Part 1: Phase III Final Studies Flight Research Facilities (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The Phase III analyses of Flight Research Facilities performed as a portion of the Hypersonic Research Facilities (HYFAC) Study are presented herein. Two attractive flight research vehicle concepts, geared to the development needs of future (1980-2n00) operational hypersonic aircraft systems, are defined. The inherent research capability of each concept is further expanded by incorporating provisions within the basic vehicle design to accommodate the testing of several additional research options. The design feasibility of this approach to achieving increased research flexibility is examined. Near term propulsion systems are employed as the basic power plants to shorten acquisition time, reduce development costs, and provide high confidence in attaining the performance capability desired, Performance is determined for each basic vehicle and for the vehicles when incorporating several optional research packages. Total program cost estimates are developed for each vehicle and for the various research options. This study provides the necessary framework for the formulation of an attractive and needed flight research program which is a key element in the systematic development of an overall advanced research plan.
    Keywords: Aircraft Propulsion and Power
    Type: MDC-A0013-VOL-4-PT-1-PHASE-3 , NASA-CR-114327
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    NACA Investigation of a Jet-Propulsion System Applicable to Flight (1943)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Following a brief history of the NACA investigation of jet propulsion, a discussion is given of the general investigation and analysis leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made.
    Keywords: Aircraft Propulsion and Power
    Type: NACA/TR-802
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aerodynamic Heat-Power Engine Operating on a Closed Cycle (1942)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Hot-air engines with dynamic compressors and turbines offer new prospects of success through utilization of units of high efficiencies and through the employment of modern materials of great strength at high temperature. Particular consideration is given to an aerodynamic prime mover operating on a closed circuit and heated externally. Increase of the pressure level of the circulating air permits a great increase of limit load of the unit. This also affords a possibility of regulation for which the internal efficiency of the unit changes but slightly. The effect of pressure and temperature losses is investigated. A general discussion is given of the experimental installation operating at the Escher Wyss plant in Zurich for a considerable time at high temperatures.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1034 , Zeitschrift des Vereines Deutscher Lagenieure; 85; 22; 491-500
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Investigation of Single Stage Axial Fans (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The following investigations are connected with experiments on fans carried out by the author in the Gouttingen Aerodynamic Laboratory within the framework of the preliminary experiments for the new Gouttingen wind-tunnel project. A fan rotor was developed which had very high efficiency at the design point corresponding to moderate pressure and which, in addition, could operate at a proportionally high pressure, rise. To establish the determining operating factors the author carried out extensive theoretical investigation in Hannover. In this it was necessary, to depart from the usual assumption of vanishing radial velocities. The calculations were substantially lightened by the introduction of diagrams. The, first part of the.report describes the theoretical investigations; the second, the experiments carried out at Gouttingen.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1062 , Luftfahyrtforschung; 14; 7; 325-346
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Hypersonic Research Facilities Study - Volume II, Part 2: Phase I Preliminary Studies Flight Vehicle Synthesis (1970)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Airbreathing hypersonic aircraft employing liquid hydrogen fuel have the potential of satisfying a number of mission requirements in the 1980-2000 time period. However, major advances in the technological state of the art are necessary before such aircraft can be considered either feasible or practical. The objective was to assess the research and development requirements for hypersonic aircraft and based on these requirements, to provide the NASA with characteristics of a number of desirable hypersonic research facilities. The study is organized in three phases. Phase I is a preliminary analysis of a broad group of concepts. The purpose of Phase I was to compare the characteristics of these facilities considering research capability, versatility, adaptability, system confidence and costs and based on these comparisons select those facilities that appear most attractive for parametric study and further refinement in Phase II. This part of Volume II presents the results of the design and cost synthesis of the flight research facilities.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-114324 , MDC-A0013-VOL-2-PT-2-PHASE-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Performance Characteristics of an Aircraft Engine with Exhaust Turbine Supercharger, Special Report (1941)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The Pratt and Whitney Aircraft company and the Naval Aircraft Factory of the United States Navy cooperated in a laboratory and flight program of tests on an exhaust turbine supercharger. Two series of dynamometer tests of the engine super-charger combination were completed under simulated altitude conditions. One series of hot gas-chamber tests was conducted by the manufacturer of the supercharger. Flight demonstrations of the supercharger installed in a twin-engine flying boat were terminated by failure of the turbine wheels. The analysis of the results indicated that a two-stage supercharger with the first-stage exhaust turbine driven will deliver rated power for a given indicated power to a higher altitude, will operate more efficiently, and will require simpler controls than a similar engine with the first stage of the supercharger driven from the crankshaft through multispeed gears.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-194
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Wind-Tunnel Tests of Several Model Tractor-Propeller and Pusher-Propeller Wing Extension-Shaft Arrangements, Special Report (1941)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Tests were made in the 20-foot propeller-research tunnel to investigate the possibility of obtaining increased net efficiencies of propeller-nacelle units by enclosing the engines in the wings and by using extension shafts. A wing of 5-foot chord was fitted with a propeller drive assembly providing for several axial locations of tractor propellers and pusher propellers. A three-blade 4-foot propeller and a three-blade 3 1/2-foot propeller of special design were tested in this wing with spinners and fairings ranging in diameter from 6 to 16 inches. A 16-inch NACA cowling was tested for comparative purposes. Two types of cuffs were also employed. It was found that the net efficiency of a conventional round-shank propeller mounted on an extension shaft in front of or behind a wing increased with an increase in the diameter of the spinner and the shaft housing within the scope of the tests. The largest spinner used had a diameter that might favorably compare with that of a radial engine cowling. The efficiencies for the pusher position appeared to be more critically affected by spinner size than those for the tractor position. The spinners with large diameters for the pusher position resulted in a higher efficiency than those for the corresponding tractor arrangements; the reverse was true for the small spinners. The use of propeller cuffs in combination with a spinner of small diameter generally resulted in net efficiencies that were comparable with those found for the large-spinner combinations.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-196
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Experimental Determination of Exhaust Gas Thrust, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This investigation presents the results of tests made on a radial engine to determine the thrust that can be obtained from the exhaust gas when discharged from separate stacks and when discharged from the collector ring with various discharge nozzles. The engine was provided with a propeller to absorb the power and was mounted on a test stand equipped with scales for measuring the thrust and engine torque. The results indicate that at full open throttle at sea level, for the engine tested, a gain in thrust horsepower of 18 percent using separate stacks, and 9.5 percent using a collector ring and discharge nozzle, can be expected at an air speed of 550 miles per hour.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-139
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Flight Tests of Exhaust Gas Jet Propulsion, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Flight test s were conducted on the XP-41 airplane, equipped with a Pratt & Whitney R1830-19, 14-cylinder, air-cooled engine, to determine the increase in flight speed obtainable by the use of individual exhaust stacks directed rearwardly to obtain exhaust-gas thrust. Speed increases up to 18 miles per hour at 20,000 feet altitude were obtained using stacks having an exit area of 3.42 square inches for each cylinder. A slight increase in engine power and decrease in cylinder temperature at a given manifold pressure were obtained with the individual stacks as compared with a collector-ring installation. Exhaust-flame visibility was quite low, particularly in the rich range of fuel-air ratios.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-165
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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