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  • Other Sources  (10)
  • 2005-2009  (4)
  • 1950-1954  (6)
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  • 1
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    Investigation of acceleration characteristics of a single-spool turbojet engine (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Operation of a single-spool turbojet engine with constant exhaust-nozzle area was investigated at one flight condition. Data were obtained by subjecting the engine to approximate-step changes in fuel flow, and the information necessary to show the relations of acceleration to the sensed engine variables was obtained. These data show that maximum acceleration occurred prior to stall and surge. In the low end of the engine-speed range the margin was appreciable; in the high-speed end the margin was smaller but had not been completely defined by these data. Data involving acceleration as a function of speed, fuel flow, turbine-discharge temperature, compressor-discharge pressure, and thrust have been presented and an effort has been made to show how a basic control system could be improved by addition of an override in which the acceleration characteristic is used not only to prevent the engine from entering the surge region but also to obtain acceleration along the maximum acceleration line during throttle bursts.
    Type: NACA-RM-E53H26
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Analysis of Experimental Sea-level Transient Data and Analog Method of Obtaining Altitude Response for Turbine-propeller Engine with Relay-type Speed Control (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Correlation has been established between transient engine and control data obtained experimentally and data obtained by simulating the engine and control with an analog computer. This correlation was established at sea-level conditions for a turbine-propeller engine with a relay-type speed control. The behavior of the controlled engine at altitudes of 20,000 and 35,000 feet was determined with an analog computer using the altitude pressure and temperature generalization factors to calculate the new engine constants for these altitudes. Because the engine response varies considerably at altitude some type of compensation appears desirable and four methods of compensation are discussed.
    Type: NACA-RM-E51D26
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Performance of three high-recovery-factor thermocouple probes for room-temperature operation (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-E50I29
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental Analysis of a Pressure-sensitive System for Sensing Gas Temperature (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-2043
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Analog study of interacting and noninteracting multiple-loop control systems for turbojet engines (1954)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-3112
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Active Flow Control at Low Reynolds Numbers on a NACA 0015 Airfoil (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results from a low Reynolds number wind tunnel experiment on a NACA 0015 airfoil with a 30% chord trailing edge flap tested at deflection angles of 0, 20, and 40 are presented and discussed. Zero net mass flux periodic excitation was applied at the ap shoulder to control flow separation for flap deflections larger than 0. The primary objective of the experiment was to compare force and moment data obtained from integrating surface pressures to data obtained from a 5-component strain-gage balance in preparation for additional three-dimensional testing of the model. To achieve this objective, active flow control is applied at an angle of attack of 6 where published results indicate that oscillatory momentum coefficients exceeding 1% are required to delay separation. Periodic excitation with an oscillatory momentum coefficient of 1.5% and a reduced frequency of 0.71 caused a significant delay of separation on the airfoil with a flap deflection of 20. Higher momentum coefficients at the same reduced frequency were required to achieve a similar level of flow attachment on the airfoil with a flap deflection of 40. There was a favorable comparison between the balance and integrated pressure force and moment results.
    Keywords: Aircraft Stability and Control
    Type: 26th AIAA Applied Aerodynamics Conference; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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    NASA TECHNICAL REPORTS
  • 7
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    Active Control of Separation From the Flap of a Supercritical Airfoil (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Zero-mass-flux periodic excitation was applied at several regions on a simplified high-lift system to delay the occurrence of flow separation. The NASA Energy Efficient Transport (EET) supercritical airfoil was equipped with a 15% chord simply hinged leading edge flap and a 25% chord simply hinged trailing edge flap. Detailed flow features were measured in an attempt to identify optimal actuator placement. The measurements included steady and unsteady model and tunnel wall pressures, wake surveys, arrays of surface hot-films, flow visualization, and particle image velocimetry (PIV). The current paper describes the application of active separation control at several locations on the deflected trailing edge flap. High frequency (F(+) approximately equal to 10) and low frequency amplitude modulation (F(+) sub AM approximately equal to 1) of the high frequency excitation were used for control. It was noted that the same performance gains were obtained with amplitude modulation and required only 30% of the momentum input required by pure sine excitation.
    Keywords: Aircraft Stability and Control
    Type: AIAA Journal; 44; 1; 34-41
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  • 8
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    High-Lift System for a Supercritical Airfoil: Simplified by Active Flow Control (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Active flow control wind tunnel experiments were conducted in the NASA Langley Low-Turbulence Pressure Tunnel using a two-dimensional supercritical high-lift airfoil with a 15% chord hinged leading-edge flap and a 25% chord hinged trailing-edge flap. This paper focuses on the application of zero-net-mass-flux periodic excitation near the airfoil trailing edge flap shoulder at a Mach number of 0.1 and chord Reynolds numbers of 1.2 x 10(exp 6) to 9 x 10(exp 6) with leading- and trailing-edge flap deflections of 25 deg. and 30 deg., respectively. The purpose of the investigation was to increase the zero-net-mass-flux options for controlling trailing edge flap separation by using a larger model than used on the low Reynolds number version of this model and to investigate the effect of flow control at higher Reynolds numbers. Static and dynamic surface pressures and wake pressures were acquired to determine the effects of flow control on airfoil performance. Active flow control was applied both upstream of the trailing edge flap and immediately downstream of the trailing edge flap shoulder and the effects of Reynolds number, excitation frequency and amplitude are presented. The excitations around the trailing edge flap are then combined to control trailing edge flap separation. The combination of two closely spaced actuators around the trailing-edge flap knee was shown to increase the lift produced by an individual actuator. The phase sensitivity between two closely spaced actuators seen at low Reynolds number is confirmed at higher Reynolds numbers. The momentum input required to completely control flow separation on the configuration was larger than that available from the actuators used.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2007-0707 , 45th AIAA Aerospace Sciences Meeting and Exhibit; Jan 08, 2007 - Jan 11, 2007; Reno, NV; United States
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    NASA TECHNICAL REPORTS
  • 9
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    Preliminary Performance Data on Westinghouse Electronic Power Regulator Operating on J34-WE-32 Turbojet Engine in Altitude Wind Tunnel (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The behavior of the Westinghouse electronic power regulator operating on a J34-WE-32 turbojet engine was investigated in the NACA Lewis altitude wind tunnel at the request of the Bureau of Aeronautics, Department of the Navy. The object of the program was to determine the, steady-state stability and transient characteristics of the engine under control at various altitudes and ram pressure ratios, without afterburning. Recordings of the response of the following parameters to step changes in power lever position throughout the available operating range of the engine were obtained; ram pressure ratio, compressor-discharge pressure, exhaust-nozzle area, engine speed, turbine-outlet temperature, fuel-valve position, jet thrust, air flow, turbine-discharge pressure, fuel flow, throttle position, and boost-pump pressure. Representative preliminary data showing the actual time response of these variables are presented. These data are presented in the form of reproductions of oscillographic traces.
    Keywords: Aerodynamics
    Type: NACA-RM-SE50J11
    Format: application/pdf
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  • 10
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    Multi-Resolution Planning in Large Uncertain Domains (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This project spanned three and one half years of research. This report covers three major lines of work that were done most recently and reported on in a talk given by the PI at NASA Ames on March 23, 2004. There are have been additional publications related to this work (Lane & Kaelbling, 2001a, 2001b, 2002; Zettlemoyer, Pasula, & Kaelbling, 2003; Gardiol & Kaelbling, 2003; Pasula, Zettlemoyer, & Kaelbling, 2004).
    Keywords: Numerical Analysis
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