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  • 1
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    Comparison of X-31 Flight and Ground-Based Yawing Moment Asymmetries at High Angles of Attack (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-28
    Description: Significant yawing moment asymmetries were encountered during the high-angle-of-attack envelope expansion of the two X-31 aircraft. These asymmetries caused position saturations of the thrust-vectoring vanes and trailing-edge flaps during some stability-axis rolling maneuvers at high angles of attack. The two test aircraft had different asymmetry characteristics, and ship 2 has asymmetries that vary as a function of Reynolds number. Several aerodynamic modifications have been made to the X-31 forebody with the goal of minimizing the asymmetry. These modifications include adding transition strips on the forebody and noseboom, using two different length strakes, and increasing nose bluntness. Ultimately, a combination of forebody strakes, nose blunting, and noseboom transition strips reduced the yawing moment asymmetry enough to fully expand the high-angle-of-attack envelope. Analysis of the X-31 flight data is reviewed and compared to wind-tunnel and water-tunnel measurements. Several lessons learned are outlined regarding high-angle-of-attack configuration design and ground testing.
    Keywords: Aircraft Design, Testing and Performance
    Type: Symposium on Advanced Flow Management. Part A: Vortex Flows and High Angle of Attack for Military Vehicles. Part B: Heat Transfer and Cooling in Propulsion and Power Systems; RTO-MP-069(I)-Pt-A-B
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Enabling Advanced Wind-Tunnel Research Methods Using the NASA Langley 12-Foot Low Speed Tunnel (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Design of Experiment (DOE) testing methods were used to gather wind tunnel data characterizing the aerodynamic and propulsion forces and moments acting on a complex vehicle configuration with 10 motor-driven propellers, 9 control surfaces, a tilt wing, and a tilt tail. This paper describes the potential benefits and practical implications of using DOE methods for wind tunnel testing - with an emphasis on describing how it can affect model hardware, facility hardware, and software for control and data acquisition. With up to 23 independent variables (19 model and 2 tunnel) for some vehicle configurations, this recent test also provides an excellent example of using DOE methods to assess critical coupling effects in a reasonable timeframe for complex vehicle configurations. Results for an exploratory test using conventional angle of attack sweeps to assess aerodynamic hysteresis is summarized, and DOE results are presented for an exploratory test used to set the data sampling time for the overall test. DOE results are also shown for one production test characterizing normal force in the Cruise mode for the vehicle.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper-2014-3000 , NF1676L-17827 , AIAA Aviation Technology, Integration and Operations (ATIO) Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States|AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014); Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aircraft Configured for Flight in an Atmosphere Having Low Density (2012)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An aircraft is configured for flight in an atmosphere having a low density. The aircraft includes a fuselage, a pair of wings, and a rear stabilizer. The pair of wings extends from the fuselage in opposition to one another. The rear stabilizer extends from the fuselage in spaced relationship to the pair of wings. The fuselage, the wings, and the rear stabilizer each present an upper surface opposing a lower surface. The upper and lower surfaces have X, Y, and Z coordinates that are configured for flight in an atmosphere having low density.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Active Wing Shaping Control Concept Using Composite Lattice-Based Cellular Materials (2015)
    In:  CASI
    Details
    Publication Date: 2019-09-05
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN20702 , 2015 LEARN/Seedling Technical Seminar; Jan 13, 2015 - Jan 15, 2015; Moffett Field, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    NASA's Learn-to-Fly Project Overview (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-16
    Description: Learn-to-Fly (L2F) is an advanced technology development effort aimed at assessing the feasibility of real-time, self-learning flight vehicles. Specifically, research has been conducted on merging real-time aerodynamic modeling, learning adaptive control, and other disciplines with the goal of using this learn to fly methodology to replace the current iterative vehicle development paradigm, substantially reducing the typical ground and flight testing requirements for air vehicle design. Recent activities included an aggressive flight test program with unique fully autonomous fight test vehicles to rapidly advance L2F technology. This paper presents an overview of the project and key components.
    Keywords: Aircraft Design, Testing and Performance
    Type: NF1676L-28629 , AIAA Aviation and Aeronautics Forum (Aviation 2018); Jul 25, 2018 - Jul 29, 2018; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Comparison of X-31 Flight and Ground-Based Yawing Moment Asymmetries at High Angles of Attack (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Significant yawing moment asymmetries were encountered during the high-angle-of-attack envelope expansion of the two X-31 aircraft. These asymmetries caused position saturations of the thrust-vectoring vanes and trailing-edge flaps during some stability-axis rolling maneuvers at high angles of attack. The two test aircraft had different asymmetry characteristics, and ship two has asymmetries that vary as a function of Reynolds number. Several aerodynamic modifications have been made to the X-31 forebody with the goal of minimizing the asymmetry. These modifications include adding transition strips on the forebody and noseboom, using two different length strakes, and increasing nose bluntness. Ultimately, a combination of forebody strakes, nose blunting, and noseboom transition strips reduced the yawing moment asymmetry enough to fully expand the high-angle-of-attack envelope. Analysis of the X-31 flight data is reviewed and compared to wind-tunnel and water-tunnel measurements. Several lessons learned are outlined regarding high-angle-of-attack configuration design and ground testing.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2001-210393 , H-2455 , NAS 1.15:210393 , Paper MP-69-P-42 , Advanced Flow Management Symposium; May 07, 2001 - May 11, 2001; Loen; Norway
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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