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  • Other Sources  (68)
  • AIRCRAFT
  • Aircraft Propulsion and Power
  • GENERAL
  • ddc:330
  • 1995-1999  (34)
  • 1955-1959  (34)
  • 1
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    External-store drag reduction at transonic and low supersonic Mach numbers by application of Baldwin's moment-of-area rule (1955)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: NACA Conf. on Aerodyn. of High Speed Aircraft; p 93-103
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Ducted-Fan Engine Acoustic Predictions using a Navier-Stokes Code (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: A Navier-Stokes computer code is used to predict one of the ducted-fan engine acoustic modes that results from rotor-wake/stator-blade interaction. A patched sliding-zone interface is employed to pass information between the moving rotor row and the stationary stator row. The code produces averaged aerodynamic results downstream of the rotor that agree well with a widely used average-passage code. The acoustic mode of interest is generated successfully by the code and is propagated well upstream of the rotor; temporal and spatial numerical resolution are fine enough such that attenuation of the signal is small. Two acoustic codes are used to find the far-field noise. Near-field propagation is computed by using Eversman's wave envelope code, which is based on a finite-element model. Propagation to the far field is accomplished by using the Kirchhoff formula for moving surfaces with the results of the wave envelope code as input data. Comparison of measured and computed far-field noise levels show fair agreement in the range of directivity angles where the peak radiation lobes from the inlet are observed. Although only a single acoustic mode is targeted in this study, the main conclusion is a proof-of-concept: Navier-Stokes codes can be used both to generate and propagate rotor/stator acoustic modes forward through an engine, where the results can be coupled to other far-field noise prediction codes.
    Keywords: Aircraft Propulsion and Power
    Type: Journal of Sound and Vibration; Volume 123; No. 4; 643-664
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    INVESTIGATION OF STATIC PRESSURES AND BOUNDARY-LAYER CHARACTERISTICS ON THE FORWARD PARTS OF NINE FUSELAGES OF VARIOUS CROSS-SECTIONAL SHAPES AT M INFINITY EQUAL 2.01 (1957)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Boundary layer characteristics of fuselages of various cross sectional shapes at static pressure
    Keywords: AIRCRAFT
    Type: NACA-RM-L56I13
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    AERODYNAMIC CHARACTERISTICS OF SOME FAMILIES OF BLUNT BODIES AT TRANSONIC SPEEDS (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Static stability and drag characteristics of blunt bodies at transonic speed
    Keywords: AIRCRAFT
    Type: NASA-MEMO-10-28-58L
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    PERFORMANCE OF AN ALL-INTERNAL CONICAL COMPRESSION INLET WITH ANNULAR THROAT BLEED AT MACH NUMBER 5.0 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Internal compression inlet with throat bleed-off at hypersonic flow
    Keywords: AIRCRAFT
    Type: NACA-RM-E58E14
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A Mode Detection Method Using the Azimuthal Directivity of a Turbofan Model (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The azimuthal, far field directivity of a scale fan model was measured in high resolution. The model is a 12 inch diameter rotor with 16 blades followed by 40 stator vanes. The tests were conducted at the nominal 100% speed corresponding to a tip speed of 905 ft/sec. Measurement of the radiated sound field, forward of the fan, was made in an anechoic chamber with an inflow control device and a baffle separating the aft and forward radiated interaction noise. The acoustic field was surveyed with a circular hoop array of 16 microphones which was moved to 14 axial stations. At each axial station the hoop was rotated in half-degree increments to take 736 points in the azimuthal angle. In addition to sound pressure level, the phase angle relative to a reference microphone was measured at each point. The sound pressure level is shown to vary in patterns by 10-15 dB especially for the fundamental tone but also for the first and second harmonic. A far field mode detection method has been developed and used with the data which determines the modes generated by the fan and which then interact to form the azimuthal directivity.
    Keywords: Aircraft Propulsion and Power
    Type: AIAA Paper 99-1954
    Format: application/pdf
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  • 7
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    Evaluation of Water Injection Effect on NO(x) Formation for a Staged Gas Turbine Combustor (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NO(x) emission control by water injection on a staged turbine combustor (STC) was modeled using the KIVA-2 code with modification. Water is injected into the rich-burn combustion zone of the combustor by a single nozzle. Parametric study for different water injection patterns was performed. Results show NO(x) emission will decrease after water being injected. Water nozzle location also has significant effect for NO formation and fuel ignition. The chemical kinetic model is also sensitive to the excess water. Through this study, a better understanding of the physics and chemical kinetics is obtained, this will enhance the STC design process.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-204498 , NAS 1.26:204498 , AIAA Paper 96-0706 , Aerospace Sciences; Jan 15, 1996 - Jan 18, 1996; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    BladeCAD: An Interactive Geometric Design Tool for Turbomachinery Blades (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A new metthodology for interactive design of turbomachinery blades is presented. Software implementation of the meth- ods provides a user interface that is intuitive to aero-designers while operating with standardized geometric forms. The primary contribution is that blade sections may be defined with respect to general surfaces of revolution which may be defined to represent the path of fluid flow through the turbomachine. The completed blade design is represented as a non-uniform rational B-spline (NURBS) surface and is written to a standard IGES file which is portable to most design, analysis, and manufacturing applications.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-107262 , E-10327 , NAS 1.15:107262 , Gas Turbine and Aeroengine Congress; Jun 10, 1996 - Jun 13, 1996; Birmingham; United Kingdom
    Format: application/pdf
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  • 9
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    An Evaluation of Aircraft Emissions Inventory Methodology by Comparisons with Reported Airline Data (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: This report provides results of work done to evaluate the calculation methodology used in generating aircraft emissions inventories. Results from the inventory calculation methodology are compared to actual fuel consumption data. Results are also presented that show the sensitivity of calculated emissions to aircraft payload factors. Comparisons of departures made, ground track miles flown and total fuel consumed by selected air carriers were made between U.S. Dept. of Transportation (DOT) Form 41 data reported for 1992 and results of simplified aircraft emissions inventory calculations. These comparisons provide an indication of the magnitude of error that may be present in aircraft emissions inventories. To determine some of the factors responsible for the errors quantified in the DOT Form 41 analysis, a comparative study of in-flight fuel flow data for a specific operator's 747-400 fleet was conducted. Fuel consumption differences between the studied aircraft and the inventory calculation results may be attributable to several factors. Among these are longer flight times, greater actual aircraft weight and performance deterioration effects for the in-service aircraft. Results of a parametric study on the variation in fuel use and NOx emissions as a function of aircraft payload for different aircraft types are also presented.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/CR-1999-209480 , Rept-99B00077 , NAS 1.26:209480
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Evaluation of Water Injection Effect on NO(x) Formation for a Staged Gas Turbine Combustor (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NO(x) emission control by water injection on a staged turbine combustor (STC) was modeled using the KIVA-2 code with modification. Water is injected into the rich-burn combustion zone of the combustor by a single nozzle. Parametric study for different water injection patterns was performed. Results show NO(x) emission will decrease after water being injected. Water nozzle location also has significant effect for NO formation and fuel ignition. The chemical kinetic model is also sensitive to the excess water. Through this study, a better understanding of the physics and chemical kinetics is obtained, this will enhance the STC design process.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-204769 , NAS 1.26:204769 , AIAA Paper 96-0706 , Aerospace Sciences Meeting and Exhibit; Jan 15, 1996 - Jan 18, 1996; Reno, NV; United States
    Format: application/pdf
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