Add to ORKGAn investigation of the performance of a 16-inch ram jet engine having a single oblique-shock all-external compression inlet designed for a flight Mach number of 1.8, was conducted in the NACA Lewis 8-by 6-foot supersonic wind tunnel. Data were obtained at Mach numbers from 1.5 to 2.0 and angles of attack from 0 degrees to 10 degrees. Three exit nozzles were used; a cylindrical extension of the combustion chamber, a 4 degrees half-angle converging nozzle with a 0.71 contraction ratio, and a graphite converging-diverging nozzle having a 0.71 contraction ratio plus reexpansion to essentially major body diameter
Performance of four experimentally investigated axially symmetric spike-type nose inlets is compared...
During a free-jet investigation of a 28-inch ram-jet engine at a Mach number of 2.35, flow pulsation...
An experimental investigation was conducted to determine the performance characteristics an underslu...
An investigation of the performance of a 16-inch ram jet engine having a single oblique-shock all-ex...
An investigation was conducted in the NACA Lewis 10- by 10-foot supersonic wind tunnel to evaluate t...
An experimental investigation to determine the external and internal flow characteristics of a typic...
Data obtained from the NACA air-launched ram-jet program are summarized with emphasis placed upon th...
An investigation was conducted in the 8- by 6-foot supersonic wind tunnel on the external and intern...
Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.4...
An analytical investigation was made of the performance of isolated ram-jet engines in the flight Ma...
An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Ma...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was ...
A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone bounda...
An evaluation of the effect of geometric design variables on the performance of a16-inch-diameter ra...
Performance of four experimentally investigated axially symmetric spike-type nose inlets is compared...
During a free-jet investigation of a 28-inch ram-jet engine at a Mach number of 2.35, flow pulsation...
An experimental investigation was conducted to determine the performance characteristics an underslu...
An investigation of the performance of a 16-inch ram jet engine having a single oblique-shock all-ex...
An investigation was conducted in the NACA Lewis 10- by 10-foot supersonic wind tunnel to evaluate t...
An experimental investigation to determine the external and internal flow characteristics of a typic...
Data obtained from the NACA air-launched ram-jet program are summarized with emphasis placed upon th...
An investigation was conducted in the 8- by 6-foot supersonic wind tunnel on the external and intern...
Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.4...
An analytical investigation was made of the performance of isolated ram-jet engines in the flight Ma...
An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Ma...
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an ...
A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was ...
A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone bounda...
An evaluation of the effect of geometric design variables on the performance of a16-inch-diameter ra...
Performance of four experimentally investigated axially symmetric spike-type nose inlets is compared...
During a free-jet investigation of a 28-inch ram-jet engine at a Mach number of 2.35, flow pulsation...
An experimental investigation was conducted to determine the performance characteristics an underslu...