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  • 1
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    Predicted and measured XB-70 ground-to-ground engine noise (1968)
    In:  CASI
    Details
    Publication Date: 2006-03-01
    Description: Predicted and measured ground noise effects of B-70 aircraft engine
    Keywords: AIRCRAFT
    Type: PROGR. OF NASA RES. RELATING TO NOISE ALLEVIATION OF LARGE SUBSONIC JET AIRCRAFT 1968; P 423-434
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Externally blown flap impingement noise (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Tests of the noise produced by the impingement of the jet exhaust on the wing and flap for an externally blown flap system were conducted with a CF700 turbofan engine and an F-111B wing panel. The noise produced with a daisy nozzle installed on the engine was greater than that produced by a conical nozzle at the same thrust. The presence of the wing next to the test nozzles increased the noise, as did increasing the flap deflection angle. Compared with the conical nozzle, the daisy nozzle produced slightly less noise at a flap deflection of 60 deg but produced more noise at the lower flap deflections tested. Tests showed that the single-slotted flap deflected 60 deg, produced less noise than the double-slotted flaps. Also, maintaining the maximum distance between the exit nozzle and flap system resulted in a minor reduction in noise.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 427-441
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The X-29 flight-research program (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The X-29 experimental aircraft, which is a technology integration and evaluation platform for such features as static longitudinal instability, sweptforward wings and three-surface longitudinal control, offers an opportunity to validate the entire aircrft design process through careful correlation and comparison of flight test results with wind tunnel results and design predictions. Attention is presently given to the design features of the aircraft, which encompass supercritical airfoils, digital flight control, and aeroelastically tailored composite wings, as well as to the flight test program that was formulated to investigate the interactions and relative merits of these design features, in light of data gathered by carefully positioned sensors.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA Student Journal (ISSN 0001-1452); 22; 2-12
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    X-29 flight - Acid test for design predictions (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The X-29 flight test data are being disseminated to interested industrial and military users as fast as it becomes available. The aircraft is extensively instrumented with accelerometers and pressure sensors and optical sensors for measuring wing deflection. The thoroughness of preflight preparations permitted a rapid advance through initial test checkpoints, which have both confirmed many predictions and revealed several discrepancies. The flight envelope had been expanded to Mach 1.1 and an altitude of 40,000 ft by December 1985. Notably, the X-29 has provided in-flight data which could not be faithfully depicted in a simulator, e.g., flare procedures during landing, and has shown that the stability adjustments, although adequate for controlling the aircraft, are not rapid enough to offer a satisfactory margin of harmony. The tests are now being performed in the transonic regime, where supercritical airfoil and forward swept wing drag reduction become significant factors.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace America (ISSN 0740-722X); 24; 40-42
    Format: text
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  • 5
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    Summary of results of NASA F-15 flight research program (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: NASA conducted a multidisciplinary flight research program on the F-15 airplane. The program began in 1976 when two preproduction airplanes were obtained from the U.S. Air Force. Major projects involved stability and control, handling qualities, propulsion, aerodynamics, propulsion controls, and integrated propulsion-flight controls. Several government agencies and aerospace contractors were involved. In excess of 330 flights were flown, and over 85 papers and reports were published. This document describes the overall program, the projects, and the key results. The F-15 was demonstrated to be an excellent flight research vehicle, producing high-quality results.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-9761
    Format: text
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  • 6
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    Digital electronic engine control history (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Full authority digital electronic engine controls (DEECs) were studied, developed, and ground tested because of projected benefits in operability, improved performance, reduced maintenance, improved reliability, and lower life cycle costs. The issues of operability and improved performance, however, are assessed in a flight test program. The DEEC on a F100 engine in an F-15 aircraft was demonstrated and evaluated. The events leading to the flight test program are chronicled and important management and technical results are identified.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-2 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 15-31
    Format: application/pdf
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  • 7
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    Performance improvements of a highly integrated digital electronic control system for an F-15 airplane (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The NASA highly integrated digital electronic control (HIDEC) program is structured to conduct flight research into the benefits of integrating an aircraft flight control system with the engine control system. A brief description of the HIDEC system installed on an F-15 aircraft is provided. The adaptive engine control system (ADECS) mode is described in detail, together with simulation results and analyses that show the significant excess thrust improvements achievable with the ADECS mode. It was found that this increased thrust capability is accompanied by reduced fan stall margin and can be realized during flight conditions where engine face distortion is low. The results of analyses and simulations also show that engine thrust response is improved and that fuel consumption can be reduced. Although the performance benefits that accrue because of airframe and engine control integration are being demonstrated on an F-15 aircraft, the principles are applicable to advanced aircraft such as the advanced tactical fighter and advanced tactical aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-86748 , H-1312 , NAS 1.15:86748 , AIAA PAPER 85-1876
    Format: application/pdf
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  • 8
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    Landing approach airframe noise measurements and analysis (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flyover measurements of the airframe noise produced by the AeroCommander, JetStar, CV-990, and B-747 airplanes are presented for various landing approach configurations. Empirical and semiempirical techniques are presented to correlate the measured airframe noise with airplane design and aerodynamic parameters. Airframe noise for the jet-powered airplanes in the clean configuration (flaps and gear retracted) was found to be adequately represented by a function of airplane weight and the fifth power of airspeed. Results show the airframe noise for all four aircraft in the landing configuration (flaps extended and gear down) also varied with the fifth power of airspeed, but this noise level could not be represented by the addition of a constant to the equation for clean-configuration airframe noise.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-TP-1602
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Review of aircraft noise propagation (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The current state of knowledge about the propagation of aircraft noise was reviewed. The literature on the subject is surveyed and methods for predicting the most important and best understood propagation effects are presented. Available empirical data are examined and the data's general validity is assessed. The methods used to determine the loss of acoustic energy due to uniform spherical spreading, absorption in a homogeneous atmosphere, and absorption due to ground cover are presented. A procedure for determining ground induced absorption as a function of elevation angle between source and receiver is recommended. Other factors that affect propagation, such as refraction and scattering due to turbulence, which were found to be less important for predicting the propagation of aircraft noise, are also evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-56033
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Preliminary measurements of aircraft airframe noise with the NASA CV-990 aircraft (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight tests were conducted in a CV-990 jet transport with engines at idle power to investigate aircraft airframe noise. Test results showed that airframe noise was measured for the aircraft in the landing configuration. The results agreed well with the expected variation with the fifth power of velocity. For the aircraft in the clean configuraton, it was concluded that airframe noise was measured only at higher airspeeds with engine idle noise present at lower speeds. The data show that landing gear and flaps make a significant contribution to airframe noise.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-TM-X-73116 , A-6506
    Format: application/pdf
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