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  • 1
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    High-temperature Strain Sensor and Mounting Development (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes Government Work Package Task 29 (GWP29), whose purpose was to develop advanced strain gage technology in support of the National Aerospace Plane (NASP) Program. The focus was on advanced resistance strain gages with a temperature range from room temperature to 2000 F (1095 C) and on methods for reliably attaching these gages to the various materials anticipated for use in the NASP program. Because the NASP program required first-cycle data, the installed gages were not prestabilized or heat treated on the test coupons before first-cycle data were recorded. NASA Lewis Research Center, the lead center for GWP29, continued its development of the palladium-chromium gage; NASA Langley Research Center investigated a new concept gage using Kanthal A1; and the NASA Dryden Flight Research Center chose the well-known BCL-3 iron-chromium-aluminum gage. Each center then tested all three gages. The parameters investigated were apparent strain, drift strain, and gage factor as a function of temperature, plus gage size and survival rate over the test period. Although a significant effort was made to minimize the differences in test equipment between the three test sites (e.g., the same hardware and software were used for final data processing), the center employed different data acquisition systems and furnace configurations so that some inherent differences may be evident in the final results.
    Keywords: Instrumentation and Photography
    Type: NASA-TP-3540 , NAS 1.60:3540 , NASP-TM-1186 , E-9513
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A High Altitude-Low Reynolds Number Aerodynamic Flight Experiment (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: A sailplane is currently being developed at NASA's Dryden Flight Research Center to support a high altitude flight experiment. The purpose of the experiment is to measure the performance characteristics of an airfoil at altitudes between 100,000 and 70,000 feet at Mach numbers between 0.65 and 0.5. The airfoil lift and drag are measured from pilot and static pressures. The location of the separation bubble and vortex shedding are measured from a hot film strip. The details of the flight experiment are presented. A comparison of several estimates of the airfoil performance is also presented. The airfoil, APEX-16, was designed by Drela (MIT) with his MSES code. A two dimensional Navier-Stokes analysis has been performed by Tatineni and Zhong (UCLA) and another at the Dryden Flight Research Center. The role these analysis served to define the experiment is discussed.
    Keywords: Aerodynamics
    Type: Applied Aerodynamics; Jun 28, 1999 - Jul 01, 1999; Norfolk, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    In-Flight Capability for Evaluating Skin-Friction Gages and Other Near-Wall Flow Sensors (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An 8-in.-square boundary-layer sensor panel has been developed for in-flight evaluation of skin-friction gages and other near-wall flow sensors on the NASA Dryden Flight Research Center F-15B/Flight Test Fixture (FTF). Instrumentation on the sensor panel includes a boundary-layer rake, temperature sensors, static pressure taps, and a Preston tube. Space is also available for skin-friction gages or other near-wall flow sensors. Pretest analysis of previous F-15B/FTF flight data has identified flight conditions suitable for evaluating skin-friction gages. At subsonic Mach numbers, the boundary layer over the sensor panel closely approximates the two-dimensional (2D), law-of-the-wall turbulent boundary layer, and skin-friction estimates from the Preston tube and the rake (using the Clauser plot method) can be used to evaluate skin-friction gages. At supersonic Mach numbers, the boundary layer over the sensor panel becomes complex, and other means of measuring skin friction are needed to evaluate the accuracy of new skin-friction gages. Results from the flight test of a new rubber-damped skin-friction gage confirm that at subsonic Mach numbers, nearly 2D, law-of-the-wall turbulent boundary layers exist over the sensor panel. Sensor panel data also show that this new skin-friction gage prototype does not work in flight.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/TM-2003-210738 , H-2518 , NAS 1.15:210738 , AIAA Paper 2003-0741 , 41st AIAA Aerospace Sciences Meeting and Exhibit; Jan 06, 2003 - Jan 09, 2003; Reno, NV; United States
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    NASA TECHNICAL REPORTS
  • 4
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    Design and Predictions for a High-Altitude (Low-Reynolds-Number) Aerodynamic Flight Experiment (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experiment. The experiment will measure the performance parameters of an airfoil at high altitudes (70,000 to 100,000 ft), low Reynolds numbers (200,000 to 700,000), and high subsonic Mach numbers (0.5 and 0.65). The airfoil section lift and drag are determined from pitot and static pressure measurements. The locations of the separation bubble, Tollmien-Schlichting boundary layer instability frequencies, and vortex shedding are measured from a hot-film strip. The details of the planned flight experiment are presented. Several predictions of the airfoil performance are also presented. Mark Drela from the Massachusetts Institute of Technology designed the APEX-16 airfoil, using the MSES code. Two-dimensional Navier-Stokes analyses were performed by Mahidhar Tatineni and Xiaolin Zhong from the University of California, Los Angeles, and by the authors at NASA Dryden.
    Keywords: Aerodynamics
    Type: NASA/TM-1999-206579 , NAS 1.15:206579 , H-2340 , AIAA Paper 99-3183 , 14th Computational Fluid Dynamics; Jun 28, 1999 - Jul 01, 1999; Norfolk, VA; United States|17th Applied Aerodynamics; Jun 28, 1999 - Jul 01, 1999; Norfolk, VA; United States
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    NASA TECHNICAL REPORTS
  • 5
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    Design and Predictions for High-Altitude (Low Reynolds Number) Aerodynamic Flight Experiment (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experiment. The experiment will measure the performance parameters or an airfoil at high altitudes (70,000 - 100,000 ft), low Reynolds numbers (2 x 10(exp 5) - 7 x 10(exp 5)), and high subsonic Mach numbers (0.5 and 0.65). The airfoil section lift and drag are determined from pilot and static pressure measurements. The locations of the separation bubble, Tollmien-Schlichting boundary-layer instability frequencies, and vortex shedding are measured from a hot-film strip. The details of the planned flight experiment are presented as well as several predictions of the airfoil performance.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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