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  • 1
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    USB environment measurements based on full-scale static engine ground tests (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Flow turning parameters, static pressures, surface temperatures, surface fluctuating pressures and acceleration levels were measured in the environment of a full-scale upper surface blowing (USB) propulsive lift test configuration. The test components included a flightworthy CF6-50D engine, nacelle, and USB flap assembly utilized in conjunction with ground verification testing of the USAF YC-14 Advanced Medium STOL Transport propulsion system. Results, based on a preliminary analysis of the data, generally show reasonable agreement with predicted levels based on model data. However, additional detailed analysis is required to confirm the preliminary evaluation, to help delineate certain discrepancies with model data, and to establish a basis for future flight test comparisons.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 479-496
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Static performance and noise tests on a thrust reverser for an augmentor wing aircraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 1/3 scale model static test program was conducted to measure the noise levels and reverse thrust performance characteristics of wing-mounted thrust reverser that could be used on an advanced augmentor wing airplane. The configuration tested represents only the most fundamental designs where installation and packaging restraints are not considered. The thrust reverser performance is presented in terms of horizontal, vertical, and resultant effectiveness ratios and the reverser noise is compared on the basis of peak perceived noise level (PNL) and one-third octave band data (OASPL). From an analysis of the model force and acoustic data, an assessment is made on the stopping distance versus noise for a 90,900 kg (200,000 lb) airplane using this type of thrust reverser.
    Keywords: AIRCRAFT
    Type: NASA-CR-137561 , D6-41926
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Noise and static performance characteristics of a STOL aircraft jet flap (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Static noise and performance tests were conducted on a 1/4-scale jet flap model with a multilobe nozzle of array area ratio of 2.7. The model nozzle and flap tested were a two-dimensional section of a distributed blowing system similar to previously investigated augmentor wing systems without the upper shroud and intake door. Noise data were measured with the nozzle alone and also during attached flow conditions with the flap at two turning angles representing takeoff and approach conditions. The noise data are scaled to a 200,000-lb TOGW four-engine airplane and are presented in terms of perceived noise level and one-third octave band sound pressure level. Comparisons are made with the noise levels produced by an augmentor wing airplane fitted with a three-element acoustically lined augmentor flap. The static performance is presented in terms of thrust recovery and effective turning angle.
    Keywords: ACOUSTICS
    Type: NASA-CR-137581 , D6-42312
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Static noise tests on augmentor wing jet STOL research aircraft (C8A Buffalo) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are presented for full scale ground static acoustic tests of over-area conical nozzles and a lobe nozzle installed on the Augmentor Wing Jet STOL Research Aircraft, a modified C8A Buffalo. The noise levels and spectrums of the test nozzles are compared against those of the standard conical nozzle now in use on the aircraft. Acoustic evaluations at 152 m (500 ft), 304 m (1000 ft), and 1216 m (4000 ft) are made at various engine power settings with the emphasis on approach and takeoff power. Appendix A contains the test log and propulsion calculations. Appendix B gives the original test plan, which was closely adhered to during the test. Appendix C describes the acoustic data recording and reduction systems, with calibration details.
    Keywords: AIRCRAFT
    Type: NASA-CR-137520 , D6-41324-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Test of acoustic tone source and propulsion performance of C8A Buffalo suppressor nozzle (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are presented for a static acoustic and propulsion performance ground test conducted at the Boeing hot nozzle facility on the C8A Buffalo noise suppressor nozzle. Various methods to remove a nozzle-associated 2000-Hz tone are evaluated. Results of testing this rectangular-array lobed nozzle for propulsion performance and acoustic directivity are reported. Recommendations for future nozzle modifications and further testing are included. Appendix A contains the test plan. Appendix B presents the test log. Appendix C contains plots of the one-third octave sound pressure levels recorded during the test. Appendix D describes the acoustic data recording and reduction systems. The performance data is tabulated in Appendix E.
    Keywords: AIRCRAFT
    Type: NASA-CR-137521 , D6-41324-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Jet noise suppressor nozzle development for augmentor wing jet STOL research aircraft (C-8A Buffalo) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Noise and performance test results are presented for a full-scale advanced design rectangular array lobe jet suppressor nozzle (plain wall and corrugated). Flight design and installation considerations are also discussed. Noise data are presented in terms of peak PNLT (perceived noise level, tone corrected) suppression relative to the existing airplane and one-third octave-band spectra. Nozzle performance is presented in terms of velocity coefficient. Estimates of the hot thrust available during emergency (engine out) with the suppressor nozzle installed are compared with the current thrust levels produced by the round convergent nozzles.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-137522 , D6-41324-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Static tests of a 0.7 scale augmentor wing flap for the modified C-8A airplane - Test results and analysis (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Static tests of augmentor-wing flap system for modified C-8A jet STOL research airplane using 0.7 scale model
    Keywords: AIRCRAFT
    Type: NASA-CR-114315 , D6-24850
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    USB environment measurements based on full-scale static engine ground tests (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Flow turning parameters, static pressures, surface temperatures, surface fluctuating pressures and acceleration levels were measured in the environment of a full-scale upper surface blowing (USB) propulsive-lift test configuration. The test components included a flightworthy CF6-50D engine, nacelle and USB flap assembly utilized in conjunction with ground verification testing of the USAF YC-14 Advanced Medium STOL Transport propulsion system. Results, based on a preliminary analysis of the data, generally show reasonable agreement with predicted levels based on model data. However, additional detailed analysis is required to confirm the preliminary evaluation, to help delineate certain discrepancies with model data and to establish a basis for future flight test comparisons.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-624 , Propulsion Conference; Jul 26, 1976 - Jul 29, 1976; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Design and performance of the propulsion system for the quiet short-haul research aircraft /QSRA/ (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the design and performance of the Quiet Short-Haul Research Aircraft (QSRA) propulsion system. A discussion of the mixed-flow boundary layer control (BLC) system, which uses high and low pressure engine bleed air, is included. This system seriously affected propulsion system performance, particularly engine acceleration characteristics, requiring an integration of BLC system and powerplant controls. Funding limitations for the QSRA Project prevented extensive full-scale testing and systems mockups, resulting in a high reliance on small-scale tests and analytical techniques. Ground tests of the actual aircraft systems showed that the extrapolation of small-scale tests and analytical techniques were in good agreement with measured full-scale results.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 79-1313 , AIAA, SAE, and ASME, Joint Propulsion Conference; Jun 18, 1979 - Jun 20, 1979; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Design integration and noise studies for jet STOL aircraft. Task 7C: Augmentor wing cruise blowing valveless system. Volume 1: Static testing of augmentor noise and performance (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Static performance and acoustic tests were conducted on a two-dimensional one-third-scale augmentor flap model that simulated a cruise blowing augmentor system designed for a scale augmentor flap model that simulated a cruise blowing augmentor, which offers a degree of 150-passenger STOL airplane. The cruise blowing augmentor, which offers a degree of simplicity by requiring no fan air diverter valves, was simulated by fitting existing lobe suppressor nozzles with new nozzle fairings. Flow turning performance of the cruise blowing augmentor was measured through a large range of flap deflection angles. The noise suppression characteristics of a multilayer acoustic lining installed in the augmentor were also measured.
    Keywords: AIRCRAFT
    Type: NASA-CR-114622 , D6-41216-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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