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  • 1
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    Experimental and analytical studies of flow through a ventral and axial exhaust nozzle system for STOVL aircraft (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flow through a combined ventral and axial exhaust nozzle system was studied experimentally and analytically. The work is part of an ongoing propulsion technology effort at NASA Lewis Research Center for short takeoff, vertical landing (STOVL) aircraft. The experimental investigation was done on the NASA Lewis Powered Lift Facility. The experiment consisted of performance testing over a range of tailpipe pressure ratios from 1 to 3.2 and flow visualization. The analytical investigation consisted of modeling the same configuration and solving for the flow using the PARC3D computational fluid dynamics program. The comparison of experimental and analytical results was very good. The ventral nozzle performance coefficients obtained from both the experimental and analytical studies agreed within 1.2 percent. The net horizontal thrust of the nozzle system contained a significant reverse thrust component created by the flow overturning in the ventral duct. This component resulted in a low net horizontal thrust coefficient. The experimental and analytical studies showed very good agreement in the internal flow patterns.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2135
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Performance characteristics of a one-third-scale, vectorable ventral nozzle for SSTOVL aircraft (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Several proposed configurations for supersonic short takeoff, vertical landing aircraft will require one or more ventral nozzles for lift and pitch control. The swivel nozzle is one possible ventral nozzle configuration. A swivel nozzle (approximately one-third scale) was built and tested on a generic model tailpipe. This nozzle was capable of vectoring the flow up to + or - 23 deg from the vertical position. Steady-state performance data were obtained at pressure ratios to 4.5, and pitot-pressure surveys of the nozzle exit plane were made. Two configurations were tested: the swivel nozzle with a square contour of the leading edge of the ventral duct inlet, and the same nozzle with a round leading edge contour. The swivel nozzle showed good performance overall, and the round-leading-edge configuration showed an improvement in performance over the square-leading-edge configuration.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-2271
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Experimental performance of three design factors for ventral nozzles for SSTOVL aircraft (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental study of three variations of a ventral nozzle system for supersonic short-takeoff and vertical-landing (SSTOVL) aircraft was performed at the NASA LeRC Powered Lift Facility. These test results include the effects of an annular duct flow into the ventral duct, a blocked tailpipe, and a short ventral duct length. An analytical study was also performed on the short ventral duct configuration using the PARC3D computational dynamics code. Data presented include pressure losses, thrust and flow performance, internal flow visualization, and pressure distributions at the exit plane of the ventral nozzle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-105697 , E-7085 , NAS 1.15:105697 , AIAA PAPER 92-3789 , Joint Propulsion Conference and Exhibit
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Internal reversing flow in a tailpipe offtake configuration for SSTOVL aircraft (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A generic one-third scale model of a tailpipe offtake system for a supersonic short takeoff vertical landing (SSTOVL) aircraft was tested at LeRC Powered Lift Facility. The model consisted of a tailpipe with twin elbows, offtake ducts, and flow control nozzles, plus a small ventral nozzle and a blind flange to simulate a blocked cruise nozzle. The offtake flow turned through a total angle of 177 degrees relative to the tailpipe inlet axis. The flow split was 45 percent to each offtake and 10 percent to the ventral nozzle. The main test objective was to collect data for comparison to the performance of the same configuration predicted by a computational fluid dynamics (CFD) analysis. Only the experimental results are given - the analytical results are published in a separate paper. Performance tests were made with unheated air at tailpipe-to-ambient pressure ratios up to 5. The total pressure loss through the offtakes was as high as 15.5 percent. All test results are shown as graphs, contour plots, and wall pressure distributions. The complex flow patterns in the tailpipe and elbows at the offtake openings are described with traversing flow angle probe and paint streak flow visualization data.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3790
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Computational and experimental investigation of subsonic internal reversing flows (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The flow inside a model exhaust configuration was studied using both experimental and computational techniques. The hardware was tested at the NASA Lewis Research Center's Powered Lift Facility at tailpipe total pressure to ambient static pressure ratios ranging from 1.0 to 5.0. The flow simulations were obtained using the two 3-D Navier-Stokes CFD codes run on the Lewis Cray Y-MP computer. Both codes produced oscillatory solutions due to the inflow boundary condition reflecting acoustic waves. The CFD solutions correctly predicted the flow separation along the inside elbow of the takeoff and also along the walls of the ventral duct. Mass flow rates were overpredicted due to underprediction of the turbulent energy dissipation and subsequent total pressure loss.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 92-3791
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Experimental performance of three design factors for ventral nozzles for SSTOVL aircraft (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental study of three variations of a ventral nozzle system for supersonic short-takeoff and vertical-landing (SSTOVL) aircraft was performed at the NASA LeRC Powered Lift Facility. These test results include the effects of an annular duct flow into the ventral duct, a blocked tailpipe, and a short ventral duct length. An analytical study was also performed on the short ventral duct configuration using the PARC3D computational dynamics code. Data presented include pressure losses, thrust and flow performance, internal flow visualization, and pressure distributions at the exit plane of the ventral nozzle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3789
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Experimental performance of a ventral nozzle with pitch and yaw vectoring capability for SSTOVL aircraft (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Aircraft with supersonic, short takeoff and vertical landing capability have been proposed to replace some of the current high-performance aircraft. Several of these configurations use a ventral nozzle in the lower fuselage, aft of the center of gravity, for lift or pitch control. Internal vanes canted at 20 deg were added to a swivel-type ventral nozzle and tested at tailpipe to ambient pressure ratios up to 5.0 on the Powered Lift Facility at NASA Lewis Research Center. The addition of sets of four or seven vanes decreased the discharge coefficient of the nozzle by at least 6 percent and did not effect the thrust coefficient. Side force produced by the nozzle with vanes was 14 percent or more of the vertical force. In addition, this side force caused only a smalll loss in vertical force in comparison to the nozzle without vanes. The net thrust force was 8 deg from the vertical for four vanes and 10.5 deg for seven.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 931412 , SAE, Aerospace Atlantic Conference & Exposition; Apr 20, 1993 - Apr 23, 1993; Dayton, OH; United States|(ISSN 0148-7191); 10 p.
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Effects of flow-path variations on internal reversing flow in a tailpipe offtake configuration for ASTOVL aircraft (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A one-third-scale model of a generic tailpipe offtake system for an advanced short takeoff, vertical landing (ASTOVL) aircraft was tested at the NASA Lewis Research Center Powered Lift Facility. The basic model consisted of a tailpipe with a center body to form an annulus simulating turbine outflow with no swirl; twin offtake ducts with elbows at the ends to turn the flow to a downward direction; flow control nozzles at the ends of the elbows; and a blind flange at the end of the tailpipe to simulate a closed cruise nozzle. The offtake duct-to-tailpipe diameter ratio was 0.74. Modifications of a generic nature were then made to this basic configuration to measure the effects of flow-path changes on the flow and pressure-loss characteristics. The modifications included adding rounded entrances at the forward edges of the offtake openings, blocking the tailpipe just aft the openings instead of at the cruise nozzle, changing the location of the openings along the tailpipe, removing the center body, and varying the Mach number (flow rate) over a wide range in the tailpipe ahead of the openings by changing the size of the flow control nozzles. The tests were made with unheated air at tailpipe-to-ambient pressure ratios from 1.4 to 5. Results are presented and compared with performance graphs, total-pressure contour plots, paint streak flow visualization photographs, and a flow-angle probe traverse at the offtake entrance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 93-2438 , AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit; Jun 28, 1993 - Jun 30, 1993; Monterey, CA; United States|; 22 p.
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Experimental and analytical studies of flow through a ventral and axial exhaust nozzle system for STOVL aircraft (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Flow through a combined ventral and axial exhaust nozzle system was studied experimentally and analytically. The work is part of an ongoing propulsion technology effort at NASA Lewis Research Center for short takeoff, vertical landing (STOVL) aircraft. The experimental investigation was done on the NASA Lewis Powered Lift Facility. The experiment consisted of performance testing over a range of tailpipe pressure ratios from 1 to 3.2 and flow visualization. The analytical investigation consisted of modeling the same configuration and solving for the flow using the PARC3D computational fluid dynamics program. The comparison of experimental and analytical results was very good. The ventral nozzle performance coefficients obtained from both the experimental and analytical studies agreed within 1.2 percent. The net horizontal thrust of the nozzle system contained a significant reverse thrust component created by the flow overturning in the ventral duct. This component resulted in a low net horizontal thrust coefficient. The experimental and analytical studies showed very good agreement in the internal flow patterns.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-104364 , E-6160 , NAS 1.15:104364 , AIAA PAPER 91-2135 , Joint Propulsion Conference; Jun 24, 1991 - Jun 27, 1991; Sacramento, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Overview of STOVL aircraft propulsion research offtakes and vertical lift systems (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The overall Short Takeoff and Vertical Landing (STOVL) Aircraft Propulsion Research program includes key technologies involving offtake systems, vertical lift systems, hot gas ingestion, STOVL augmentors, and integrated flight propulsion controls. A part of the NASA Lewis work involving STOVL aircraft propulsion systems is presented with the emphasis on component-level experiments and analysis related to offtakes and vertical lift systems.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-106387 , E-8207 , NAS 1.15:106387 , AIAA PAPER 93-4865 , International Powered Lift Conference; Dec 01, 1993 - Dec 03, 1993; Santa Clara, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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