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  • Aircraft Propulsion and Power
  • 1970-1974  (4)
  • 1935-1939  (5)
  • 1
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    H-guide with Laminated Dielectric Slab (1970)
    In:  CASI
    Details
    Publication Date: 2015-02-11
    Description: Hybrid waveguide /H-guide/ with laminated dielectric slab
    Keywords: Aircraft Propulsion and Power
    Type: STUDY OF RECTANGULAR-GUIDE-LIKE STRUCT. FOR MILLIMETER WAVE TRANSMISSION 15 JUN. 1970; P 6-12
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Hypersonic Research Facilities Study - Volume III, Part 2: Phase II Parametric Studies Flight Vehicle Synthesis (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    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 was a preliminary analysis of a broad group of concepts which were reduced to seven flight research facilities and eleven ground research facilities for Phase II study. The purpose of Phase II was to perform parametric studies to refine the facility designs and obtain sensitivity information in the neighborhood of "near optimum" designs, and to select those facilities that appear most attractive in the sense of research potential vs cost for further refinement in Phase III. This part of Volume III presents the results of the synthesis of the flight research facilities.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-114326 , MDC-A0013-VOL-3-PT-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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
  • 4
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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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  • 5
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    Tandem Air Propellers - II (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Tests of three-blade, adjustable-pitch counterrotating tandem model propellers, adjusted to absorb equal power at maximum efficiency of the combination, were made at Stanford University. The aerodynamic characteristics, for blade-angle settings of 15, 25, 35, 45, 55, and 65 degrees at 0.75R of the forward propeller and for diameters spacings of 8-1/2, 15 and 30% were compared with those of three-blade and six-blade propellers of the same blade form. It was found that, in order to realize the condition of equal power at maximum efficiency, the blade angles for the rear propeller must be generally less than for the forward propeller, the difference increasing the blade angle. The tests showed that, at maximum efficiency, the tandem propellers absorb about double the power of three-blade propellers and about 8% more power than six-blade propellers having the pitch of the forward propeller of the tandem combination. The maximum efficiency of the tandem propellers was found to be from 2-15% greater than for six-blade propellers, the difference varying directly with blade angle. It was also found that the maximum efficiency of the tandem propellers was greater than that of a three-blade propeller for blade angles at 0.75R of 25 degrees or more. The difference in maximum efficiency again varied directly with blade angle, being about 9% for 65 degrees at 0.75R.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-126
    Format: application/pdf
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  • 6
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    Engine Operation in Flight for Minimum Fuel Consumption (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Engine and airplane performance data have been gathered from various sources and analyzed to determine indications of the most economical methods of flight operation from a consideration of fuel expenditure. The analysis includes the influence of such facts as fuel-air ratio, engine speed, engine knock, altitude, cylinder cooling, spark timing, and limits of cruising brake mean effective pressure. The results indicate that the cheapest power is obtained with approximately correct mixture at low engine speed and highest permissible manifold pressure. If more power is desired, the methods of obtaining it are, in order of fuel economy: (a) increasing the engine speed and maintaining safe cylinder temperatures by cooling; (b) retarding the spark or cooling further to permit higher manifold pressure; and, (c) riching the mixture. The analysis further shows that the maximum time endurance of flight occurs at the air speed corresponding to minimum thrust horsepower required and with minimum practicable engine speed. Maximum mileage per pound of fuel is obtained at slightly higher air speed. The fuel-air ratio should be approximately the theoretically correct ratio in both cases. For an engine equipped with a geared supercharger, as in the example presented, and with knock as the limiting condition, a comparison of operation at sea level and at 6,000 feet shoes flight at altitude to be more economical on the basis of both range and endurance.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-134
    Format: application/pdf
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  • 7
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    Drag and Propulsive Characteristics of Air-Cooled Engine-Nacelle Installations for Large Airplanes, Special Report (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation is in progress in the NACA full-scale wind tunnel to determine the drag and propulsive efficiency of nacelle sizes. In contrast with the usual tests with a single nacelle, these tests were conducted with nacelle-propeller installations on a large model of a 4-engine airplane. Data are presented on the first part of the investigation, covering seven nacelle arrangements with nacelle diameters from 0.53 to 1.5 times the wing thickness. These ratios are similar to those occurring on airplane weighing from about 20 to 100 tons. The results show that the drag, the propulsive efficiency, and the overall efficiency of the various nacelle arrangements as functions of the nacelle size, the propeller position, and the airplane lift coefficient. The effect of the nacelles on the aerodynamic characteristics of the model are shown for both propeller-removed and propeller-operating conditions.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-122
    Format: application/pdf
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  • 8
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    Energy Loss, Velocity Distribution, and Temperature Distribution for a Baffled Cylinder Model, Special Report (1937)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: In the design of a cowling a certain pressure drop across the cylinders of a radial air-cooled engine is made available. Baffles are designed to make use of this available pressure drop for cooling. The problem of cooling an air-cooled engine cylinder has been treated, for the most part, from considerations of a large heat-transfer coefficient. The knowledge of the precise cylinder characteristics that give a maximum heat-transfer coefficient should be the first consideration. The next problem is to distribute this ability to cool so that the cylinder cools uniformly. This report takes up the problem of the design of a baffle for a model cylinder. A study has been made of the important principles involved in the operation of a baffle for an engine cylinder and shows that the cooling can be improved 20% by using a correctly designed baffle. Such a gain is as effective in cooling the cylinder with the improved baffle as a 65% increase in pressure drop across the standard baffle and fin tips.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-64
    Format: application/pdf
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  • 9
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    Tandem Air Propellers (1937)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: Tests of 2-blade, adjustable-pitch, counterrotating tandem model propellers, adjusted to absorb equal power at maximum efficiency, were made at Stanford University. The characteristics, for 15 degrees, 25 degrees, 35 degrees, and 45 degrees pitch settings at 0.75 R of the forward propeller and for 8 1/2%, 15% and 30% diameter spacings, were compared with those of 2-blade and 4-blade propellers of the same blade form. The tests showed that the efficiency of the tandem propellers was from 0.5% to 4% greater than that of a 4-blade propeller and, at the high pitch settings, not appreciable inferior to that of a 2-blade propeller. It was found that the rear tandem propeller should be set at a pitch angle slightly less than that of the forward propeller to realize the condition of equal power at maximum efficiency. Under this condition the total power absorbed by the tandem propellers was from 3% to 9% more than that absorbed by the 4-blade propeller and about twice that absorbed by a 2-blade propeller.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-66
    Format: application/pdf
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