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  • 11
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    Direct Numerical Simulation of Acoustic Waves Interacting with a Shock Wave in a Quasi-1D Convergent-Divergent Nozzle Using an Unstructured Finite Volume Algorithm (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Numerical simulation of a very small amplitude acoustic wave interacting with a shock wave in a quasi-1D convergent-divergent nozzle is performed using an unstructured finite volume algorithm with a piece-wise linear, least square reconstruction, Roe flux difference splitting, and second-order MacCormack time marching. First, the spatial accuracy of the algorithm is evaluated for steady flows with and without the normal shock by running the simulation with a sequence of successively finer meshes. Then the accuracy of the Roe flux difference splitting near the sonic transition point is examined for different reconstruction schemes. Finally, the unsteady numerical solutions with the acoustic perturbation are presented and compared with linear theory results.
    Keywords: ACOUSTICS
    Type: NASA-TM-107070 , NAS 1.15:107070 , E-9934 , Joint Fluids Engineering Conference; Aug 13, 1995 - Aug 18, 1995; Hilton Head, SC; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Some practical turbulence modeling options for Reynolds-averaged full Navier-Stokes calculations of three-dimensional flows (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: New turbulence modeling options recently implemented for the 3-D version of Proteus, a Reynolds-averaged compressible Navier-Stokes code, are described. The implemented turbulence models include: the Baldwin-Lomax algebraic model, the Baldwin-Barth one-equation model, the Chien k-epsilon model, and the Launder-Sharma k-epsilon model. Features of this turbulence modeling package include: well documented and easy to use turbulence modeling options, uniform integration of turbulence models from different classes, automatic initialization of turbulence variables for calculations using one- or two-equation turbulence models, multiple solid boundaries treatment, and fully vectorized L-U solver for one- and two-equation models. Validation test cases include the incompressible and compressible flat plate turbulent boundary layers, turbulent developing S-duct flow, and glancing shock wave/turbulent boundary layer interaction. Good agreement is obtained between the computational results and experimental data. Sensitivity of the compressible turbulent solutions with the method of y(sup +) computation, the turbulent length scale correction, and some compressibility corrections are examined in detail. The test cases show that the highly optimized one-and two-equation turbulence models can be used in routine 3-D Navier-Stokes computations with no significant increase in CPU time as compared with the Baldwin-Lomax algebraic model.
    Keywords: AERODYNAMICS
    Type: NASA-TM-106399 , E-8231 , NAS 1.15:106399 , AIAA PAPER 93-2964 , Fluid Dynamics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Conceptual Design for a Dual-Bell Rocket Nozzle System Using a NASA F-15 Airplane as the Flight Testbed (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The dual-bell rocket nozzle was first proposed in 1949, offering a potential improvement in rocket nozzle performance over the conventional-bell nozzle. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. In 2013 a proposal was constructed that offered a NASA F-15 airplane as the flight testbed, with the plan to operate a dual-bell rocket nozzle during captive-carried flight. If implemented, this capability will permit nozzle operation into an external flow field similar to that of a launch vehicle, and facilitate an improved understanding of dual-bell nozzle plume sensitivity to external flow-field effects. More importantly, this flight testbed can be utilized to help quantify the performance benefit with the dual-bell nozzle, as well as to advance its technology readiness level. This presentation provides highlights of a technical paper that outlines this ultimate goal, including plans for future flights to quantify the external flow field of the airplane near the nozzle experiment, as well as details on the conceptual design for the dual-bell nozzle cold-flow propellant feed system integration within the NASA F-15 Propulsion Flight Test Fixture. The current study shows that this concept of flight research is feasible, and could result in valuable flight data for the dual-bell nozzle.
    Keywords: Spacecraft Propulsion and Power; Launch Vehicles and Launch Operations
    Type: DFRC-E-DAA-TN16580 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
    Format: application/pdf
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  • 14
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    Proposed Flight Research of a Dual-Bell Rocket Nozzle Using the NASA F-15 Airplane (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: For more than a half-century, several types of altitude-compensating rocket nozzles have been proposed and analyzed, but very few have been adequately tested in a relevant flight environment. One type of altitude-compensating nozzle is the dual-bell rocket nozzle, which was first introduced into literature in 1949. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. This presentation proposes a method for conducting testing and research with a dual-bell rocket nozzle in a flight environment. We propose to leverage the existing NASA F-15 airplane and Propulsion Flight Test Fixture as the flight testbed, with the dual-bell nozzle operating during captive-carried flights, and with the nozzle subjected to a local flow field similar to that of a launch vehicle. The primary objective of this effort is not only to advance the technology readiness level of the dual-bell nozzle, but also to gain a greater understanding of the nozzle mode transitional sensitivity to local flow-field effects, and to quantify the performance benefits with this technology. The predicted performance benefits are significant, and may result in reducing the cost of delivering payloads to low-Earth orbit.
    Keywords: Aircraft Design, Testing and Performance; Spacecraft Propulsion and Power
    Type: DFRC-E-DAA-TN10146 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference (JPC); Jul 14, 2013 - Jul 17, 2013; San Jose, California; United States
    Format: application/pdf
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  • 15
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    Longitudinal Aerodynamic Modeling of the Adaptive Compliant Trailing Edge Flaps on a GIII Airplane and Comparisons to Flight Data (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Discuss ACTE aerodynamic modeling efforts and provide comparisons of predictions to flight results for lift and pitching moment increments.
    Keywords: Aircraft Design, Testing and Performance; Aircraft Stability and Control; Aerodynamics
    Type: DFRC-E-DAA-TN32815 , AIAA Aviation 2016 Conference; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
    Format: application/pdf
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  • 16
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    Aerodynamic Flight-Test Results for the Adaptive Compliant Trailing Edge (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aerodynamics
    Type: DFRC-E-DAA-TN32736 , AIAA Aviation 2016 Conference; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
    Format: application/pdf
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  • 17
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    Aerodynamic Flight-Test Results for the Adaptive Compliant Trailing Edge (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The aerodynamic effects of compliant flaps installed onto a modified Gulfstream III airplane were investigated. Analyses were performed prior to flight to predict the aerodynamic effects of the flap installation. Flight tests were conducted to gather both structural and aerodynamic data. The airplane was instrumented to collect vehicle aerodynamic data and wing pressure data. A leading-edge stagnation detection system was also installed. The data from these flights were analyzed and compared with predictions. The predictive tools compared well with flight data for small flap deflections, but differences between predictions and flight estimates were greater at larger deflections. This paper describes the methods used to examine the aerodynamics data from the flight tests and provides a discussion of the flight-test results in the areas of vehicle aerodynamics, wing sectional pressure coefficient profiles, and air data.
    Keywords: Aerodynamics
    Type: DFRC-E-DAA-TN31619 , Aviation 2016; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
    Format: application/pdf
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  • 18
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    Analysis of Low-Speed Stall Aerodynamics of a Swept Wing with Seamless Flaps (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Computational fluid dynamics (CFD) analysis was conducted to study the low-speed stall aerodynamics of a Gulfstream G-III airplane (Gulfstream Aerospace Corporation, Savannah, Georgia) swept wing modified with an experimental seamless, compliant flap called the Adaptive Compliant Trailing Edge (ACTE) flap. The stall characteristics of the modified ACTE wing were analyzed and compared with the unmodified, clean wing at the flight speed of 120 knots and altitude of 2300 feet above mean sea level, in free air as well as in ground effect. A polyhedral finite-volume unstructured full Navier-Stokes CFD code, STAR-CCM (registered trademark) plus (CD-adapco [Computational Dynamics Limited, United Kingdom, and Analysis & Design Application Co., United States]), was used. Steady Reynolds-averaged Navier-Stokes CFD simulations were conducted for a clean wing and the ACTE wings at various ACTE deflection angles in free air (-2 degrees, 15 degrees, and 30 degrees) as well as in ground effect (15 degrees and 30 degrees). Solution sensitivities to grid densities were examined. In free air, the ACTE wings are predicted to stall at lower angles of attack than the clean wing. In ground effect, all wings are predicted to stall at lower angles of attack than the corresponding wings in free air. Even though the lift curves are higher in ground effect than in free air, the maximum lift coefficients for all wings are lower in ground effect. Finally, the lift increase due to ground effect for the ACTE wing is predicted to be less than the clean wing.
    Keywords: Aerodynamics
    Type: DFRC-E-DAA-TN32023 , AIAA Applied Aerodynamics Conference; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
    Format: application/pdf
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  • 19
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    Longitudinal Aerodynamic Modeling of the Adaptive Compliant Trailing Edge Flaps on a GIII Airplane and Comparisons to Flight Data (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A pair of compliant trailing edge flaps was flown on a modified GIII airplane. Prior to flight test, multiple analysis tools of various levels of complexity were used to predict the aerodynamic effects of the flaps. Vortex lattice, full potential flow, and full Navier-Stokes aerodynamic analysis software programs were used for prediction, in addition to another program that used empirical data. After the flight-test series, lift and pitching moment coefficient increments due to the flaps were estimated from flight data and compared to the results of the predictive tools. The predicted lift increments matched flight data well for all predictive tools for small flap deflections. All tools over-predicted lift increments for large flap deflections. The potential flow and Navier-Stokes programs predicted pitching moment coefficient increments better than the other tools.
    Keywords: Aircraft Design, Testing and Performance; Aerodynamics; Aircraft Stability and Control
    Type: DFRC-E-DAA-TN30942 , AIAA Aviation 2016 Conference; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
    Format: application/pdf
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  • 20
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    Proposed Flight Research of a Dual-Bell Rocket Nozzle Using the NASA F-15 Airplane (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: For more than a half-century, several types of altitude-compensating rocket nozzles have been proposed and analyzed, but very few have been adequately tested in a relevant flight environment. One type of altitude-compensating nozzle is the dual-bell rocket nozzle, which was first introduced into literature in 1949. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. This paper proposes a method for conducting testing and research with a dual-bell rocket nozzle in a flight environment. We propose to leverage the existing NASA F-15 airplane and Propulsion Flight Test Fixture as the flight testbed, with the dual-bell nozzle operating during captive-carried flights, and with the nozzle subjected to a local flow field similar to that of a launch vehicle. The primary objective of this effort is not only to advance the technology readiness level of the dual-bell nozzle, but also to gain a greater understanding of the nozzle mode transitional sensitivity to local flow-field effects, and to quantify the performance benefits with this technology. The predicted performance benefits are significant, and may result in reducing the cost of delivering payloads to low-Earth orbit.
    Keywords: Aircraft Design, Testing and Performance
    Type: DFRC-E-DAA-TN9734 , 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Jun 24, 2013; San Jose, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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