Author : Leroy L. Presley
Publisher :
Page : 50 pages
File Size : 10,45 MB
Release : 1960
Category : Aerodynamics
ISBN :
[PDF] A Comparison Of The Performance Of Four Side Mounted Inlets Over A Mach Number Range Of 088 To 22 And Angles Of Attack To 14 eBook
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A Comparison of the Performance of Four Side-mounted Inlets Over a Mach Number Range of 0.88 to 2.2 and Angles of Attack to 14°
Author : Leroy L. Presley
Publisher :
Page : 58 pages
File Size : 29,45 MB
Release : 1960
Category : Aerodynamics
ISBN :
A Comparison of the Performance of Four Side-mounted Inlets Over a Mach Number Range of 0.88 to 2.2 and Angles of Attack to 14 Deg
Author :
Publisher :
Page : 58 pages
File Size : 36,76 MB
Release : 1960
Category :
ISBN :
Scientific and Technical Aerospace Reports
Author :
Publisher :
Page : 1068 pages
File Size : 37,18 MB
Release : 1965
Category : Aeronautics
ISBN :
Investigation of an Underslung Half-cone Inlet with Compression Surface Mounted Outboard from Fuselage at Mach Numbers of 1.5, 1.8, and 2.0
Author : Richard A. Yeager
Publisher :
Page : 22 pages
File Size : 25,7 MB
Release : 1958
Category : Rockets (Aeronautics)
ISBN :
Performance of Three Isentropic All Internal Compression Axisymmetric Inlets Designed for Mach 2.5
Author : Bernhard H. Anderson
Publisher :
Page : 34 pages
File Size : 12,69 MB
Release : 1960
Category : Aerodynamics, Supersonic
ISBN :
Investigation of High-angle-of-attack Performance of a 14 Degree Ramp-type Inlet in Various Circumferential Body Locations Mach Number Range 1.5 to 2.0
Author : Glenn A. Mitchell
Publisher :
Page : 34 pages
File Size : 35,33 MB
Release : 1957
Category :
ISBN :
Preliminary Investigation of Shield to Improve Angle-of-attack Performance of Nacelle-type Inlet
Author : Milton A. Beheim
Publisher :
Page : 38 pages
File Size : 17,96 MB
Release : 1957
Category : 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.
Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79
Author : Owen H. Davis
Publisher :
Page : 34 pages
File Size : 40,94 MB
Release : 1960
Category : Aerodynamics, Supersonic
ISBN :
Jane's All the World's Aircraft
Author :
Publisher :
Page : 864 pages
File Size : 32,78 MB
Release : 1989
Category : Aeronautics
ISBN :