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- Unclassified, Unlimited, Publicly available.
- Noise tests were conducted with small-scale models of externally blown-flap powered-lift systems that were subjected to simulated takeoff and landing free-stream velocities by placing the nozzle-wing models in a free jet. The nozzle configurations consisted of a conical and an 8-tube mixer nozzle. The results show that the free-stream velocity attenuates the noise from the various configurations, with the amount of attenuation depending on the flap setting. More attenuation was obtained with a flap setting of 20 degrees than with a flap setting of 60 degrees. The dynamic effect on the total attenuation caused by aircraft motion is also discussed.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19750007581.
Accession ID: 75N15653.
2d Aero-Acoustics Specialists Conf.; 24-26 Mar. 1975; Hampton, VA; United States.
- No Copyright.
View MARC record | catkey: 15741415