Preliminary Investigation Of A New Type Of Supersonic Inlet
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Preliminary Investigation of Effects of Combustion in Ram Jet on Performance of Supersonic Diffusers
| Author | : Albert H. Schroeder |
| Publisher | : |
| Total Pages | : 18 |
| Release | : 1948 |
| Genre | : Aeronautics |
| ISBN | : |
Preliminary Investigation of Shield to Improve Angle-of-attack Performance of Nacelle-type Inlet
| Author | : Milton A. Beheim |
| Publisher | : |
| Total Pages | : 38 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
An investigation was conducted at Mach numbers between 1.6 and 2.0 on the use of a shield along the upper-half periphery of the cowl of a conical inlet to improve performance at angle of attack. The best results were obtained with the shield mounted in such a manner that an air gap existed between the shield and the cowl lip. Zero-angle-of-attack performance was not appreciably affected. At an angle of attack of 8 degrees distortion was about half that without the shield, and subcritical stability was improved.
An Investigation of Several NACA 1-series Nose Inlets with and Without Protruding Central Bodies at High-subsonic Mach Numbers and at a Mach Number of 1.2
| Author | : Robert E. Pendley |
| Publisher | : |
| Total Pages | : 58 |
| Release | : 1950 |
| Genre | : Aerodynamic load |
| ISBN | : |
An investigation of three NACA 1-series nose inlets, two of which were fitted with protruded central bodies, was conducted in the Langley 8-foot high-speed tunnel. An elliptical-nose body, which had a critical Mach number approximately equal to that of one of the nose inlets, was also tested. Tests were made near zero angle of attack for a Mach number range from 0.4 to 0.925 and for the supersonic Mach number of 1.2. The inlet-velocity-ratio range extended from zero to a maximum value of 1.34. Measurements included pressure distribution, external drag, and total-pressure loss of the internal flow near the inlet. Drag was not measured for the tests at the supersonic Mach number.
