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  • 1
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    A Discrete and Distributed Steady Blowing Application on a High Reynolds Number Semispan Supercritical Wing Configuration (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The FAST-MAC circulation control model was modified to test an array of steady and unsteady actuators at realistic flight Reynolds numbers in the National Transonic Facility at the NASA Langley Research Center. Previous experiments in the FAST-MAC test series used a fullspan tapered slot, and that configuration is used as a baseline for performance and weight flow requirements. The goal of the latest experiment was to reduce the weight flow required to achieve comparable performance established by the baseline FAST-MAC data. Thirty-nine interchangeable actuator cartridges of various designs were mounted into the FAST-MAC model where the exiting jet was directed over a 15% chord simple hinged-flap. These two types of actuators were fabricated using rapid prototype techniques and their design performance was optimized for a transonic cruise configuration having a 0 flap deflection. The steady actuators were found to provide an off-design drag reduction of 5.5%, nearly equaling the drag reduction of the fullspan tapered slot configuration, but with a 69% weight flow reduction. This weight flow savings is similar to the sweeping jet actuators, but with better drag performance.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NF1676L-28921 , AIAA SciTech; Jan 08, 2018 - Jan 12, 2018; Kissimmee, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    An Active Flow Circulation Controlled Flap Concept for General Aviation Aircraft Applications (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A recent focus on revolutionary aerodynamic concepts has highlighted the technology needs of general aviation and personal aircraft. New and stringent restrictions on these types of aircraft have placed high demands on aerodynamic performance, noise, and environmental issues. Improved high lift performance of these aircraft can lead to slower takeoff and landing speeds that can be related to reduced noise and crash survivability issues. Circulation Control technologies have been around for 65 years, yet have been avoided due to trade offs of mass flow, pitching moment, perceived noise etc. The need to improve the circulation control technology for general aviation and personal air-vehicle applications is the focus of this paper. This report will describe the development of a 2-D General Aviation Circulation Control (GACC) wing concept that utilizes a pulsed pneumatic flap.
    Keywords: Aerodynamics
    Type: AIAA Paper 2002-3157 , 1st AIAA Flow Control Conference; Jun 24, 2002 - Jun 26, 2002; Saint Louis, MO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Using Computational Fluid Dynamics and Experiments to Design Sweeping Jets for High Reynolds Number Cruise Configurations (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The application of a sweeping jet actuator to a circulation control system was initiated by a risk reduction series of experiments to optimize the authority of a single sweeping jet actuator. The sweeping jet design was integrated into the existing Fundamental Aerodynamic Subsonic Transonic- Modular Active Control (FAST-MAC) model by replacing the steady blowing system with an array of thirty-nine sweeping jet cartridges. A constant slot height to wing chord ratio was similar to the steady blowing configuration resulting in each actuator having a unique in size for the sweeping jet configuration. While this paper will describe the scaling and optimization of the actuators for future high Reynolds number applications, the major focus of this effort was to target the transonic flight regime by increasing the amplitude authority of the actuator. This was accomplished by modifying the diffuser of the sweeping jet actuator, and this paper highlights twelve different diffuser designs. The experimental portion of this work was completed in the NASA Langley National Transonic Facility.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NF1676L-23034 , AIAA Aviation 2016; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Force Measurement Improvements to the National Transonic Facility Sidewall Model Support System (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The National Transonic Facility is a transonic pressurized cryogenic facility. The development of the high Reynolds number semi-span capability has advanced over the years to include transonic active flow control and powered testing using the sidewall model support system. While this system can be used in total temperatures down to -250 F for conventional unpowered configurations, it is limited to temperatures above -60 F when used with powered models that require the use of the high-pressure air delivery system. Thermal instabilities and non-repeatable mechanical arrangements revealed several data quality shortfalls by the force and moment measurement system. Recent modifications to the balance cavity recirculation system have improved the temperature stability of the balance and metric model-to-balance hardware. Changes to the mechanical assembly of the high-pressure air delivery system, particularly hardware that interfaces directly with the model and balance, have improved the repeatability of the force and moment measurement system. Drag comparisons with the high-pressure air system removed will also be presented in this paper.
    Keywords: Research and Support Facilities (Air)
    Type: NF1676L-23076 , 2016 AIAA SciTech Conference; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A Sweeping Jet Application on a High Reynolds Number Semispan Supercritical Wing Configuration (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The FAST-MAC circulation control model was modified to test an array of unsteady sweeping-jet actuators at realistic flight Reynolds numbers in the National Transonic Facility at the NASA Langley Research Center. Two types of sweeping jet actuators were fabricated using rapid prototype techniques, and directed over a 15% chord simple-hinged flap. The model was configured for low-speed high-lift testing with flap deflections of 30 deg and 60 deg, and a transonic cruise configuration having a 0 deg flap deflection. For the 30 deg flap high-lift configuration, the sweeping jets achieved comparable lift performance in the separation control regime, while reducing the mass flow by 54% as compared to steady blowing. The sweeping jets however were not effective for the 60 deg flap. For the transonic cruise configuration, the sweeping jets reduced the drag by 3.3% at an off-design condition. The drag reduction for the design lift coefficient for the sweeping jets offer is only half the drag reduction shown for the steady blowing case (6.5%), but accomplished this with a 74% reduction in mass flow.
    Keywords: Aircraft Stability and Control; Aircraft Design, Testing and Performance
    Type: NF1676L-25574 , AIAA Aviation; Jun 05, 2017 - Jun 09, 2017; Denver, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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