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  • 1
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    Preliminary results of steady state characterization of near term electric vehicle breadboard propulsion system (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The steady state test results on a breadboard version of the General Electric Near Term Electric Vehicle (ETV-1) are discussed. The breadboard was built using exact duplicate vehicle propulsion system components with few exceptions. Full instrumentation was provided to measure individual component efficiencies. Tests were conducted on a 50 hp dynamometer in a road load simulator facility. Characterization of the propulsion system over the lower half of the speed-torque operating range has shown the system efficiency to be composed of a predominant motor loss plus a speed dependent transaxle loss. At the lower speeds with normal road loads the armature chopper loss is also a significant factor. At the conditions corresponding to a cycle for which the vehicle system was specifically designed, the efficiencies are near optimum.
    Keywords: URBAN TECHNOLOGY AND TRANSPORTATION
    Type: NASA-TM-81546 , DOE/NASA/1011-31 , E-502
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Baseline tests of the EPC Hummingbird electric passenger vehicle (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The rear-mounted internal combustion engine in a four-passenger Volkswagen Thing was replaced with an electric motor made by modifying an aircraft generator and powered by 12 heavy-duty, lead-acid battery modules. Vehicle performance tests were conducted to measure vehicle maximum speed, range at constant speed, range over stop-and-go driving schedules, maximum acceleration, gradeability limit, road energy consumption, road power, indicated energy consumption, braking capability, battery charger efficiency, and battery characteristics. Test results are presented in tables and charts.
    Keywords: URBAN TECHNOLOGY AND TRANSPORTATION
    Type: NASA-TM-73760 , E-9485 , CONS/1011-5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Baseline tests of the C. H. Waterman DAF electric passenger vehicle (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An electric vehicle was tested as part of an Energy Research Development Administration (ERDA) project to characterize the state-of-the-art of electric vehicles. The Waterman vehicle performance test results are presented in this report. The vehicle is a converted four-passenger DAF 46 sedan. It is powered by sixteen 6-volt traction batteries through a three-step contactor controller actuated by a foot throttle to change the voltage applied to the 6.7 kW motor. The braking system is a conventional hydraulic braking system.
    Keywords: URBAN TECHNOLOGY AND TRANSPORTATION
    Type: NASA-TM-73757 , CONS/1011-2 , E-9388
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Baseline tests of the AM General DJ-5E electruck electric delivery van (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An electric quarter ton truck designed for use as a postal delivery vehicle was tested to characterize the state of the art of electric vehicles. Vehicle performance test results are presented. It is powered by a single-module, 54 volt industrial battery through a silicon controlled rectifier continuously adjustable controller with regenerative braking applied to a direct current compound wound motor.
    Keywords: URBAN TECHNOLOGY AND TRANSPORTATION
    Type: NASA-TM-73758 , E-9383 , CONS/1011-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Baseline tests of the Zagato Elcar electric passenger vehicle (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Elcar vehicle performance test results are presented. The Elcar Model 2000 is a two-passenger vehicle with a reinforced fiberglass body. It is powered by eight 12-volt batteries. The batteries are connected to the motor through an arrangement of contactors operated from a foot pedal in conjunction with a hand-operated switch. These contactors change the voltage applied to the 2-kilowatt motor. Acceleration tests, operating characteristics, and instrumentation are described.
    Keywords: URBAN TECHNOLOGY AND TRANSPORTATION
    Type: NASA-TM-73764 , CONS/1011-9 , E-9442
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Baseline tests of the C. H. Waterman Renault 5 electric passenger vehicle (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Waterman vehicle, a four passenger Renault 5 GTL, performance test results are presented and characterized the state-of-the-art of electric vehicles. It was powered by sixteen 6-volt traction batteries through a two-step contactor controller actuated by a foot throttle to change the voltage applied to the 6.7 -kilowatt motor. The motor output shaft was connected to a front-wheel-drive transaxle that contains a four-speed manual transmission and clutch. The braking system was a conventional hydraulic braking system.
    Keywords: URBAN TECHNOLOGY AND TRANSPORTATION
    Type: NASA-TM-73759 , E-9434 , CONS/1011-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Effect of transient winds on the flow quality of an open-circuit wind-tunnel model (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of a transient wind on the test-section flow quality of an open-circuit wind tunnel was investigated experimentally. The investigation was restricted to transient wind effects associated with the inlet. A small open-circuit wind tunnel was placed outside in the real wind environment. Test-section speed and angularity as well as wind speed and direction was measured by high-response instrumentation. The inlet configuration was varied with a set of screens, a removable honeycomb, and a removable inlet lip. Acceptable flow was obtained at all wind angles and for wind- to test-section-velocity ratios up to 0.4 with an inlet configuration having five screens, a honeycomb, and a lip. With inlet configurations sensitive to winds, a transient wind parallel to the tunnel axis produced local fluctuations in test-section speed and angularity; however, oscillation of the average test-section speed was not evident. The effect of wind direction was negligible up to wind angles of 45 deg relative to the tunnel axis. At larger wind angles, flow distortions occurred primarily on the windward side of the test section.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2538 , E-6773
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A laboratory facility for electric vehicle propulsion system testing (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The road load simulator facility located at the NASA Lewis Research Center enables a propulsion system or any of its components to be evaluated under a realistic vehicle inertia and road loads. The load is applied to the system under test according to the road load equation: F(net)=K1F1+K2F2V+K3 sq V+K4(dv/dt)+K5 sin theta. The coefficient of each term in the equation can be varied over a wide range with vehicle inertial representative of vehicles up to 7500 pounds simulated by means of flywheels. The required torque is applied by the flywheels, a hydroviscous absorber and clutch, and a drive motor integrated by a closed loop control system to produce a smooth, continuous load up to 150 horsepower.
    Keywords: URBAN TECHNOLOGY AND TRANSPORTATION
    Type: NASA-TM-81574 , DOE/NASA/1011-32 , E-544 , Intern. Congr. of Transportation; Sep 15, 1980 - Sep 17, 1980; Dearborn, MI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Effects of forward velocity on noise for a J85 turbojet engine with multitube suppressor from wind tunnel and flight tests (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Flight and wind tunnel noise tests were conducted using a J85 turbojet engine as a part of comprehensive programs to obtain an understanding of forward velocity effects on jet exhaust noise. Nozzle configurations of primary interest were a 104-tube suppressor with and without an acoustically-treated shroud. The installed configuration of the engine was as similar as possible in the flight and wind tunnel tests. Exact simultaneous matching of engine speed, exhaust velocity, and exhaust temperature was not possible, and the wind tunnel maximum Mach number was approximately 0.27, while the flight Mach number was approximately 0.37. The nominal jet velocity range was 450 to 640 m/sec. For both experiments, background noise limited the jet velocity range for which significant data could be obtained. In the present tests the observed directivity and forward velocity effects for the suppressor are more similar to predicted trends for internally-generated noise than unsuppressed jet noise.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-73542 , E-8974 , Meeting of the Acoustical Soc. of Am.; Nov 16, 1976 - Nov 19, 1976; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Effect of configuration variation on externally blown flap noise (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The sensitivity of flap interaction noise to variations in engine-under-the-wing externally blown flap geometry was investigated with a large cold-flow model. Both 2- and 3-flap wing sections (7-ft chord) with trailing flap angles up to 60 deg were employed. Exhaust nozzles included coaxial, plug, and 8- and 13-inch diameter conical configurations. These nozzles were tested at two positions below the wing. The effects of these geometry variations on noise level, directivity, and spectral shape are summarized in terms of exhaust flow parameters evaluated at the nozzle exit and at the flap impingement station. The results are also compared with limited flap noise data available from tests using real engines.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-71495 , E-7858 , Aerospace Sci. Meeting; Jan 30, 1974 - Feb 01, 1974; Washington, DC; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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