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  • 11
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    Preliminary study of a subsonic nuclear cruise airplane having a helium-cooled thermal reactor (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Keywords: GENERAL
    Type: NASA-TM-X-1667
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    GENENG 2: A program for calculating design and off-design performance of two- and three-spool turbofans with as many as three nozzles (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program which calculates steady-state design and off-design jet engine performance for two- or three-spool turbofans with one, two, or three nozzles is described. Included in the report are complete FORTRAN 4 listings of the program with sample results for nine basic turbofan engines that can be calculated: (1) three-spool, three-stream engine; (2) two-spool, three-stream, boosted-fan engine; (3) two-spool, three-stream, supercharged-compressor engine; (4) three-spool, two-stream engine; (5) two-spool, two-stream engine; (6) three-spool, three-stream, aft-fan engine; (7) two-spool, three-stream, aft-fan engine; (8) two-spool, two-stream, aft-engine; and (9) three-spool, two-stream, aft-fan engine. The simulation of other engines by using logical variables built into the program is also described.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6553 , E-6356
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    GENENG: A program for calculating design and off-design performance for turbojet and turbofan engines (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program entitled GENENG employs component performance maps to perform analytical, steady state, engine cycle calculations. Through a scaling procedure, each of the component maps can be used to represent a family of maps (different design values of pressure ratios, efficiency, weight flow, etc.) Either convergent or convergent-divergent nozzles may be used. Included is a complete FORTRAN 4 listing of the program. Sample results and input explanations are shown for one-spool and two-spool turbojets and two-spool separate- and mixed-flow turbofans operating at design and off-design conditions.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6552 , E-5867
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    NNEP: The Navy NASA Engine Program (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer code capable of simulating almost any conceivable turbine engine is described. This code uses stacked component maps and multiple flowpaths to simulate variable cycle engines with variable component geometry. It is capable of design and off-design (matching) calculations and can optimize free variables such as nozzle areas to minimize specific fuel consumption.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71857 , E-8606
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    Study of a LH2-fueled topping cycle engine for aircraft propulsion (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An analytical investigation was made of a topping cycle aircraft engine system which uses a cryogenic fuel. This system consists of a main turboshaft engine which is mechanically coupled (by cross-shafting) to a topping loop which augments the shaft power output of the system. The thermodynamic performance of the topping cycle engine was analyzed and compared with that of a reference (conventional-type) turboshaft engine. For the cycle operating conditions selected, the performance of the topping cycle engine in terms of brake specific fuel consumption (bsfc) was determined to be about 12 percent better than that of the reference turboshaft engine. Engine weights were estimated for both the topping cycle engine and the reference turboshaft engine. These estimates were based on a common shaft power output for each engine. Results indicate that the weight of the topping cycle engine is comparable to that of the reference turboshaft engine. Previously announced in STAR as N83-34942
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-2543
    Format: text
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    NASA TECHNICAL REPORTS
  • 16
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    Performance potential of gas-core and fusion rockets: A mission applications survey (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analysis of mission applications and characteristics of gas-core and fusion rockets
    Keywords: NUCLEAR ENGINEERING
    Type: NASA-TM-X-67940 , E-5547
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    Nuclear powered VTOL aircraft (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Performance characteristics of nuclear powered VTOL aircraft
    Keywords: AIRCRAFT
    Type: NASA-TM-X-52524
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    A remote augmentor lift system with a turbine bypass engine (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Two supersonic vertical takeoff or landing (VTOL) aircraft engine types, a conventional medium bypass ratio turbofan, and a turbine bypass turbojet were studied. The aircraft assumed was a clipped delta wing with canard configuration. A VTOL deck launched intercept, DLI, mission with Mach 1.6 dash and cruise segments was used as the design mission. Several alternate missions requiring extended subsonic capabilities were analyzed. Comparisons were made between the turbofan (TF) and the turbine bypass turbojet (TBE) engines in airplane types using a Remote Augmented Lift Systems, RALS and a Lift plus Lift Cruise system (L+LC). The figure of merit was takeoff gross weight for the VTOL DLI mission. The results of the study show that the turbine bypass turbojet and the conventional turbofan are competitive engines for both type of aircraft in terms of takeoff gross weight and range. However, the turbine bypass turbojet would be a simpler engine and may result in more attractive life cycle costs and reduced maintenance. The RALS and L+LC airplane types with either TBE or TF engines have approximately the same aircraft takeoff gross weight.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-82932 , E-1330 , NAS 1.15:82932 , Cong. of the Intern. Council of Aeronautical Sci. and Aircraft Systems and Technol. Meeting; Aug 22, 1982 - Aug 27, 1982; Seattle
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    NASA research in supersonic propulsion - A decade of progress (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: (Previously announced in STAR as N82-26300)
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1048 , Joint Propulsion Conference; Jun 21, 1982 - Jun 23, 1982; Cleveland, OH
    Format: text
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    NASA TECHNICAL REPORTS
  • 20
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    Computer simulation of engine systems (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The paper discusses the availability throughout the government and industry of analytical methods for calculating both the steady state and transient performance of an aircraft engine during an entire flight regime. The historical development of some of the analytical tools capable of evaluating installation effects on engine performance is traced and their present status is described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 80-0051 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
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