TEST OF ACOUSTIC TONE SOURCE PROPULSION PERFORMANCE OF C&A BUFFALO SUPPRESSOR NOZZLE

摘要

Results arc presented for a static acoustic and propulsion performance ground test conducted at the Boeing hot nozzle facility on the C8A Buffalo noise suppressor nozzle.nVarious 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 arc reported. Recommendations for future nozzle modifications and further testing are included.nAppendix 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.