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  • 1
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    Demonstration of skin friction measurements featuring in situ estimation of conduction loss using constant voltage anemometers and surface hot-films (2005)
    American Institute of Physics
    Details
    Publication Date: 2005-05-01
    Print ISSN: 0034-6748
    Electronic ISSN: 1089-7623
    Topics: Electrical Engineering, Measurement and Control Technology , Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 2
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    High angle-of-attack flush airdata sensing system (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 915-919
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Development of a pneumatic high-angle-of-attack Flush Airdata Sensing (HI-FADS) system (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The HI-FADS system design is an evolution of the FADS systems (e.g., Larson et al., 1980, 1987), which emphasizes the entire airdata system development. This paper describes the HI-FADS measurement system, with particular consideration given to the basic measurement hardware and the development of the HI-FADS aerodynamic model and the basic nonlinear regression algorithm. Algorithm initialization techniques are developed, and potential algorithm divergence problems are discussed. Data derived from HI-FADS flight tests are used to demonstrate the system accuracies and to illustrate the developed concepts and methods.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: In: Control and dynamic systems. Vol. 52 - Integrated technology methods and applications in aerospace systems design (A94-12611 02-01); p. 453-511.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Low-Boom SR-71 Modified Signature Demonstration Program (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: A flight program using the SR-71 airplane to validate sonic boom technologies for High-Speed Commercial Transport (HSCT) operation and potentially for low- or softened-boom design configurations is described. This program employs a shaped signature modification to the SR-71 airplane which is designed to demonstrate computational fluid dynamics (CFD) design technology at a full-scale HSCT operating condition of Mach 1.8 at 48,000 feet altitude. Test plans call for measurements in the near-field, at intermediate propagation altitudes, and through the more turbulent boundary layer near the Earth surface. The shaped signature modification to the airplane is comprised of added cross-section areas on the underside of the airplane forward of the wing and engine nacelles. Because the flight demonstration does not approach maximum SR-71 altitude or Mach number, the airplane provides more than adequate performance and maneuver margins for safe operation of the modified airplane. Probe airplane measurements in the near-field will use fast response pressure sensors. Far-field and ground-based boom measurements will use high response microphones or conventional sonic boom field recorders. Scope of the planned demonstration flights also includes ground level measurements during conditions which cause minimal signature distortion and conditions which cause high distortion of the signature.
    Keywords: Aircraft Design, Testing and Performance
    Type: High-Speed Research: 1994 Sonic Boom Workshop. Configuration, Design, Analysis and Testing; 237-248; NASA/CP-1999-209699
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Preliminary results from a subsonic high-angle-of-attack flush airdata sensing (HI-FADS) system - Design, calibration, algorithm development, and flight test evaluation (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A nonintrusive high angle-of-attack flush airdata sensing (HI-FADS) system was installed and flight-tested on the F-18 high alpha research vehicle. This paper discusses the airdata algorithm development and composite results expressed as airdata parameter estimates and describes the HI-FADS system hardware, calibration techniques, and algorithm development. An independent empirical verification was performed over a large portion of the subsonic flight envelope. Test points were obtained for Mach numbers from 0.15 to 0.94 and angles of attack from -8.0 to 55.0 deg. Angles of sideslip ranged from -15.0 to 15.0 deg, and test altitudes ranged from 18,000 to 40,000 ft. The HI-FADS system gave excellent results over the entire subsonic Mach number range up to 55 deg angle of attack. The internal pneumatic frequency response of the system is accurate to beyond 10 Hz.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: AIAA PAPER 90-0232
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Aerothermal test results from the second flight of the Pegasus booster (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A survey of temperature, heat-flux, and pressure measurements was obtained at speeds through Mach 8.0 on the second flight of the Pegasus air-launched space booster system. All sensors were distributed on the wing-body fairing or fillet. Sensors included thin foil-gauge thermocouples installed near the surface within the thermal protection system. Thermocouples were also installed on the surface of nonablating plugs. The resulting temperature time history allowed derivation of convective heat flux. In addition, commercially available calorimeters were installed on the fillet at selected locations. Calorimeters exhibited a larger change in measured heat flux than collocated nonablating plugs in response to particular events. Similar proportional variations in heat flux across different regions of the fillet were detected by both the calorimeters and nonablating plugs. Pressure ports were installed on some nonablating plugs to explore the effects of port protrusion and high-frequency noise on pressure requirements. The effect of port protrusion on static-pressure measurements was found to decrease with increasing Mach number. High-frequency noise suppression was found to be desirable but not required on any future flight.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-4391 , H-1827 , NAS 1.15:4391
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Failure detection and fault management techniques for flush airdata sensing systems (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Methods based on chi-squared analysis are presented for detecting system and individual-port failures in the high-angle-of-attack flush airdata sensing system on the NASA F-18 High Alpha Research Vehicle. The HI-FADS hardware is introduced, and the aerodynamic model describes measured pressure in terms of dynamic pressure, angle of attack, angle of sideslip, and static pressure. Chi-squared analysis is described in the presentation of the concept for failure detection and fault management which includes nominal, iteration, and fault-management modes. A matrix of pressure orifices arranged in concentric circles on the nose of the aircraft indicate the parameters which are applied to the regression algorithms. The sensing techniques are applied to the F-18 flight data, and two examples are given of the computed angle-of-attack time histories. The failure-detection and fault-management techniques permit the matrix to be multiply redundant, and the chi-squared analysis is shown to be useful in the detection of failures.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: AIAA PAPER 92-0263
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Preliminary results from an airdata enhancement algorithm with application to high-angle-of-attack flight (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A technique has been developed to improve the fidelity of airdata measurements during dynamic maneuvering. This technique is particularly useful for airdata measured during flight at high angular rates and high angles of attack. To support this research, flight tests using the F-18 high alpha research vehicle were conducted at the NASA Ames Research Center Dryden Flight Research Facility. A Kalman filter was used to combine information from research airdata, linear accelerometers, angular rate gyros, and attitude gyros to determine better estimates of airdata quantities such as angle of attack, angle of sideslip, airspeed, and altitude. This paper briefly develops the state and observation equations used by the Kalman filter and shows how the state and measurement covariance matrices were determined from flight data.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: AIAA PAPER 91-0672
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    The effects of pressure sensor acoustics on airdata derived from a high-angle-of-attack flush airdata sensing (HI-FADS) system (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The accuracy of a prototype nonintrusive airdata system derived for high-angle-of-attack measurements was demonstrated for quasi-steady maneuvers as great as 55 degrees during phase one of the F-18 high alpha research vehicle flight test program. This system consists of a matrix of nine pressure ports arranged in annular rings on the aircraft nose, and estimates the complete airdata set utilizing flow modeling and nonlinear regression. Particular attention is paid to the effects of acoustical distortions within the individual pressure sensors of the HI-FADS pressure matrix. A dynamic model to quantify these effects which describes acoustical distortion is developed and solved in closed form for frequency response.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: AIAA PAPER 91-0671
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    In-flight investigation of shuttle tile pressure orifice installations (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: To determine shuttle orbiter wing loads during ascent, wing load instrumentation was added to Columbia (OV-102). This instrumentation included strain gages and pressure orifices on the wing. The loads derived from wing pressure measurements taken during STS 61-C did not agree with those derived from strain gage measurements or with the loads predicted from the aerodynamic database. Anomalies in the surface immediately surrounding the pressure orifices in the thermal protection system (TPS) tiles were one possible cause of errors in the loads derived from wing pressure measurements. These surface anomalies were caused by a ceramic filler material which was installed around the pressure tubing. The filler material allowed slight movement of the TPS tile and pressure tube as the airframe flexed and bent under aerodynamic loads during ascent and descent. Postflight inspection revealed that this filler material had protruded from or receeded beneath the surface, causing the orifice to lose its flushness. Flight tests were conducted at NASA Ames Research Center Dryden Flight Research Facility to determine the effects of any anomaly in surface flushness of the orifice installation on the measured pressures at Mach numbers between 0.6 and 1.4. An F-104 aircraft with a flight test fixture mounted beneath the fuselage was used for these flights. Surface flushness anomalies typical of those on the orbiter after flight (STA 61-C) were tested. Also, cases with excessive protrusion and recession of the filler material were tested. This report shows that the anomalies in STS 61-C orifice installations adversely affected the pressure measurements. But the magnitude of the affect was not great enough to account for the discrepancies with the strain gage measurements and the aerodynamic predictions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-4219 , H-1575 , NAS 1.15:4219
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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