PDF 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° Download
- Author: Leroy L. Presley
- Publisher:
- ISBN:
- Category : Aerodynamics
- Languages : en
- Pages : 58
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
Scientific and Technical Aerospace Reports
Flight Determination of Drag and Pressure Recovery of Two Scoop Inlets Located at Maximum-body-diameter Station at Mach Numbers from 0.8 to 1.8
PDF Flight Determination of Drag and Pressure Recovery of Two Scoop Inlets Located at Maximum-body-diameter Station at Mach Numbers from 0.8 to 1.8 Download
- Author: Leonard W. Putland
- Publisher:
- ISBN:
- Category : Boundary layer control
- Languages : en
- Pages : 30
Two models each utilizing a scoop inlet located at the maximum-body-diameter station operating mass-flow ratios from 0.76 to 0.96 have been flight tested at an angle of attack of approximately zero degrees over a Mach number range from 0.8 to 1.8, and a Reynolds number range from 2,000,000 to7,000,000 based on body maximum diameter. One of the scoop inlets had a circular cross section with a boundary-layer diverter. The other scoop inlet had a semicircular cross section wrapped partly around the body with a boundary-layer splitter plate ahead of the inlet.
Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79
Performance of External-compression Bump Inlet at Mach Numbers of 1.5 to 2.0
Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99
PDF Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 Download
- Author: L. J. Obery
- Publisher:
- ISBN:
- Category : Aerodynamics, Supersonic
- Languages : en
- Pages : 72
An experimental investigation to determine the external and internal flow characteristics of a typical ram-jet-inlet configuration of an external-compression type utilizing an isentropic spike and a subsonic diffuser was conducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel. The model was investigated of a range of mass-flow ratios at angles of attack up to 10 degrees, free-stream Mach numbers of 1.59, 1.79, and 1.99, and a Reynolds number of approximately 2,400,000 based on inlet diameter.
