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  • 1
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    Aerodynamics, computers and the environment (2014)
    The Royal Society
    Details
    Publication Date: 2014-08-13
    Print ISSN: 1364-503X
    Electronic ISSN: 1471-2962
    Topics: Mathematics , Physics , Technology
    Published by The Royal Society
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    PAPER CURRENT
  • 2
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    Design Evolution and Performance Characterization of the GTX Air-Breathing Launch Vehicle Inlet (2002)
    In:  Other Sources
    Details
    Publication Date: 2011-08-23
    Description: The design and analysis of a second version of the inlet for the GTX rocket-based combine-cycle launch vehicle is discussed. The previous design did not achieve its predicted performance levels due to excessive turning of low-momentum comer flows and local over-contraction due to asymmetric end-walls. This design attempts to remove these problems by reducing the spike half-angle to 10- from 12-degrees and by implementing true plane of symmetry end-walls. Axisymmetric Reynolds-Averaged Navier-Stokes simulations using both perfect gas and real gas, finite rate chemistry, assumptions were performed to aid in the design process and to create a comprehensive database of inlet performance. The inlet design, which operates over the entire air-breathing Mach number range from 0 to 12, and the performance database are presented. The performance database, for use in cycle analysis, includes predictions of mass capture, pressure recovery, throat Mach number, drag force, and heat load, for the entire Mach range. Results of the computations are compared with experimental data to validate the performance database.
    Keywords: Launch Vehicles and Launch Operations
    Type: 26th JANNAF Airbreathing Propulsion Subcommittee Meeting; Volume 1; 107-123; CPIA-Publ-713-Vol-1
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    PARC Analysis of the NASA/GE 2D NRA Mixer/Ejector Nozzle (1999)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Interest in developing a new generation supersonic transport has increased in the past several years. Current projections indicate this aircraft would cruise at approximately Mach 2.4, have a range of 5000 nautical miles and carry at least 250 passengers. A large market for such an aircraft will exist in the next century due to a predicted doubling of the demand for long range air transportation by the end of the century and the growing influence of the Pacific Rim nations. Such a proposed aircraft could more than halve the flying time from Los Angeles to Tokyo. However, before a new economically feasible supersonic transport can be built, many key technologies must be developed. Among these technologies is noise suppression. Propulsion systems for a supersonic transport using current technology would exceed acceptable noise levels. All new aircraft must satisfy FAR 36 Stage III noise regulations. The largest area of concern is the noise generated during takeoff. A concerted effort under NASA's High Speed Research (HSR) program has begun to address the problem of noise suppression. One of the most promising concepts being studied in the area of noise suppression is the mixer/ejector nozzle. This study analyzes a typical noise suppressing mixer ejector nozzle at take off conditions, using a Full Navier-Stokes (FNS) computational fluid dynamics (CFD) code.
    Keywords: Aircraft Propulsion and Power
    Type: First NASA/Industry High Speed Research Program Nozzle Symposium; 16-1 - 16-32; NASA/CP-1999-209423
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Three-dimensional compressible turbulent computations for a diffusing S-duct (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of the present study was to evaluate the capability of the computational fluid dynamics computer program PARC3D to model flow in a typical diffusing subsonic S-duct, with strong secondary flows. This evaluation is needed to provide confidence in the analysis of aircraft inlets, which have similar geometries. The performance predictions include total pressure profiles, static pressures, velocity profiles, boundary layer data, and skin friction data. Flow in the S-duct is subsonic, and the boundary layers are assumed to be turbulent. The results for both H and O grid solutions, are compared with existing test data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4392 , E-6172 , NAS 1.26:4392
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Three-dimensional compressible turbulent computations for a nondiffusing S-duct (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The PARC3D code was used to compute the compressible turbulent flow within a three dimensional, nondiffusing S-duct. A frame of reference is provided for future computational fluid dynamics studies of internal flows with strong secondary flows and provides an understanding of the performance characteristics of a typical S-duct with attached flow. The predicted results, obtained with both H- and O-grids, are compared with the experimental wall pressure, static and total pressure fields, and velocity vectors. Additionally, computed boundary layer thickness, velocity profiles in wall coordinates, and skin friction values are presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4391 , E-6173 , NAS 1.26:4391
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Numerical Analysis of the Trailblazer Inlet Flowfield for Hypersonic Mach Numbers (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A study of the Trailblazer vehicle inlet was conducted using the Global Air Sampling Program (GASP) code for flight Mach numbers ranging from 4-12. Both perfect gas and finite rate chemical analysis were performed with the intention of making detailed comparisons between the two results. Inlet performance was assessed using total pressure recovery and kinetic energy efficiency. These assessments were based upon a one-dimensional stream-thrust-average of the axisymmetric flowfield. Flow visualization utilized to examine the detailed shock structures internal to this mixed-compression inlet. Kinetic energy efficiency appeared to be the least sensitive to differences between the perfect gas and finite rate chemistry results. Total pressure recovery appeared to be the most sensitive discriminator between the perfect gas and finite rate chemistry results for flight Mach numbers above Mach 6. Adiabatic wall temperature was consistently overpredicted by the perfect gas model for flight Mach numbers above Mach 4. The predicted shock structures were noticeably different for Mach numbers from 6-12. At Mach 4, the perfect gas and finite rate chemistry models collapse to the same result.
    Keywords: Aerodynamics
    Type: NASA/TM-1999-209654 , NAS 1.15:209654 , AIAA Paper 2000-0889 , E-12010 , 38th Aerospace Sciences Meeting; Jan 10, 2000 - Jan 13, 2000; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Inlet Development for a Rocket Based Combined Cycle, Single Stage to Orbit Vehicle Using Computational Fluid Dynamics (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Design and analysis of the inlet for a rocket based combined cycle engine is discussed. Computational fluid dynamics was used in both the design and subsequent analysis. Reynolds averaged Navier-Stokes simulations were performed using both perfect gas and real gas assumptions. An inlet design that operates over the required Mach number range from 0 to 12 was produced. Performance data for cycle analysis was post processed using a stream thrust averaging technique. A detailed performance database for cycle analysis is presented. The effect ot vehicle forebody compression on air capture is also examined.
    Keywords: Launch Vehicles and Space Vehicles
    Type: NASA/TM-1999-209279 , NAS 1.15:209279 , AIAA Paper 99-2239 , E-11744 , Joint Propulsion; Jun 20, 1999 - Jun 24, 1999; Los Angeles, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Status of Turbulence Modeling for High-Speed Propulsion Flow Problems (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics; Aerodynamics
    Type: E-664062
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Rocket-Based Combined Cycle Engine Technology Development: Inlet CFD Validation and Application (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A CFD methodology has been developed for inlet analyses of Rocket-Based Combined Cycle (RBCC) Engines. A full Navier-Stokes analysis code, NPARC, was used in conjunction with pre- and post-processing tools to obtain a complete description of the flow field and integrated inlet performance. This methodology was developed and validated using results from a subscale test of the inlet to a RBCC 'Strut-Jet' engine performed in the NASA Lewis 1 x 1 ft. supersonic wind tunnel. Results obtained from this study include analyses at flight Mach numbers of 5 and 6 for super-critical operating conditions. These results showed excellent agreement with experimental data. The analysis tools were also used to obtain pre-test performance and operability predictions for the RBCC demonstrator engine planned for testing in the NASA Lewis Hypersonic Test Facility. This analysis calculated the baseline fuel-off internal force of the engine which is needed to determine the net thrust with fuel on.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-107274 , ICOMP-96-6 , E-10342 , NAS 1.15:107274 , AIAA Paper 96-3145 , Joint Propulsion Conference; Jul 01, 1996 - Jul 03, 1996; Lake Buena Vista, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Navier-Stokes analysis of three-dimensional S-ducts (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Full 3D Navier-Stokes computational results are presented for compressible flows within nondiffusing and diffusing S-ducts. The present study provides an understanding of the performance characteristics of typical S-ducts with attached and separated flows and provides a frame of reference for future computational fluid dynamic studies of internal flows with strong secondary flows. The predicted results, which were obtained using both H- and O-grids, are compared with the experimental wall pressures, static and total pressure fields, and velocity vectors. In addition, computed boundary-layer thickness, velocity profiles in wall coordinates and skin friction values are presented. The inviscid contributions to the secondary flows are quantified. The S-duct entrance Mach number was 0.6, and the Reynolds number was 1.76 x 10 exp 6 based on the upstream duct diameter.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 30; 4; p. 526-533.
    Format: text
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    NASA TECHNICAL REPORTS
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