Some aspects of the aircraft noise problem inside high-speed jet-powered transport airplanes are presented. The airplane wing effectively shields a large portion of the airplane fuselage from the intense sounds in the jet stream of pod mounted engines located near or forward of the airplane center of gravity. Measurements of this shielding are presented. Diffraction effects in these measurements verify the distribution of energy and frequency content in the jet mixing region as reported by NACA and British sources. The pressure doubling effect at the fuselage sidewall is also evident in these measurements. Noise data obtained from continuous recordings inside a high speed jet powered airplane during a variety of flight conditions are presented. Noise inside the airplane due to turbulence in the fuselage boundary layer becomes the major noise source at high speeds and the sound levels are very high in the aft fuselage section. There is a great need for research in methods of calculating and reducing this aerodynamic boundary layer noise.