Author: Antonio FerriPublisher:
ISBN:
Category :
Languages : en
Pages : 38
Book Description
Preliminary Investigation of a New Type of Supersonic Inlet
Author: Antonio FerriA Preliminary Investigation of the Pressure Recovery of Several Two-dimensional Supersonic Inlets at a Mach of 2.01
Author: Raymond J. ComenzoPreliminary Investigation of a Variable Mass-flow Supersonic Nose Inlet
Author: Clyde HayesReport
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 22
Book Description
Preliminary Investigation of Effects of Combustion in Ram Jet on Performance of Supersonic Diffusers
Author: Albert H. SchroederPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 18
Book Description
A Preliminary Investigation of a Supersonic Air Intake Employing an Aerodynamic Compression Surface
Author: M.D. DobsonPreliminary Investigation of a Supersonic Scoop Inlet Derived from a Conical-spike Nose Inlet
Author: Charles E. WittliffPerforated Supersonic Inlet
Author: A. H. SchroederAn 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. PendleyPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 58
Book Description
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.
Preliminary Investigation of Shield to Improve Angle-of-attack Performance of Nacelle-type Inlet
Author: Milton A. BeheimPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 38
Book Description
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.