Add to ORKGUtilizing a static test stand, 6- by 9-foot wind tunnel and 13-inch circular free jet, aerodynamic and acoustic data were obtained with a convergent circular nozzle, bypass nozzle, 6-tube mixer nozzle, and velocity decay surveys with and without forward velocity. The acoustic data include total sound power, directivity and frequency spectra obtained statically and with forward velocity. The relation of aerodynamic and acoustic measurements statically and in forward flight for the various nozzle configurations are discussed
A test program was conducted in the Boeing large anechoic test chamber and the NASA-Ames 40- by 80-f...
Experimental acoustic data are presented to illustrate, at model scale, the effect of varying the no...
To determine flyover noise and thrust and to investigate whether flight velocity significantly affec...
A test program was conducted in a 40 by 80 foot wind tunnel to evaluate the effect of relative veloc...
The results of a test program conducted in the NASA Ames 40- by 80-Foot Wind Tunnel to determine the...
Experimental data of the peak axial-velocity decay in a moving airstream are presented for several t...
Acoustic data, with and without forward velocity, were obtained with a circular nozzle using a quiet...
Two spoke-type suppressor plug nozzles and a basic plug nozzle were tested for noise and thrust perf...
Acoustic shielding benefits for jet noise of engine-over-the-wing for conventional aircraft (CTOL) a...
An investigation to determine the effect of forward speed on the exhaust noise from a conical ejecto...
Jet noise spectra obtained at static conditions from an acoustic wind tunnel and an outdoor facility...
The effect of forward flight on the jet noise of coannular exhaust nozzles, suitable for Variable St...
Noise tests were conducted with small-scale models of externally blown-flap powered-lift systems tha...
A model scale flight effects test was conducted in the 40 by 80 foot wind tunnel to investigate the ...
Flight and wind tunnel noise tests were conducted using a J85 turbojet engine as a part of comprehen...
A test program was conducted in the Boeing large anechoic test chamber and the NASA-Ames 40- by 80-f...
Experimental acoustic data are presented to illustrate, at model scale, the effect of varying the no...
To determine flyover noise and thrust and to investigate whether flight velocity significantly affec...
A test program was conducted in a 40 by 80 foot wind tunnel to evaluate the effect of relative veloc...
The results of a test program conducted in the NASA Ames 40- by 80-Foot Wind Tunnel to determine the...
Experimental data of the peak axial-velocity decay in a moving airstream are presented for several t...
Acoustic data, with and without forward velocity, were obtained with a circular nozzle using a quiet...
Two spoke-type suppressor plug nozzles and a basic plug nozzle were tested for noise and thrust perf...
Acoustic shielding benefits for jet noise of engine-over-the-wing for conventional aircraft (CTOL) a...
An investigation to determine the effect of forward speed on the exhaust noise from a conical ejecto...
Jet noise spectra obtained at static conditions from an acoustic wind tunnel and an outdoor facility...
The effect of forward flight on the jet noise of coannular exhaust nozzles, suitable for Variable St...
Noise tests were conducted with small-scale models of externally blown-flap powered-lift systems tha...
A model scale flight effects test was conducted in the 40 by 80 foot wind tunnel to investigate the ...
Flight and wind tunnel noise tests were conducted using a J85 turbojet engine as a part of comprehen...
A test program was conducted in the Boeing large anechoic test chamber and the NASA-Ames 40- by 80-f...
Experimental acoustic data are presented to illustrate, at model scale, the effect of varying the no...
To determine flyover noise and thrust and to investigate whether flight velocity significantly affec...