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The External-Shock Drag of Supersonic Inlets Having Subsonic Entrance Flow

Description: Memorandum presenting a determination of the external-shock drags of supersonic inlets with circular cross sections from shadow photographs at a Mach number of 2.70 for a low-external-compression and a high-external-compression inlet. The calculated mass flow for both types of inlets showed reasonably good agreement with the measured values. Results as determined by the characteristics method and the approximate method are provided.
Date: December 20, 1950
Creator: Nucci, Louis M.
Partner: UNT Libraries Government Documents Department

The Origin of Aerodynamic Instability of Supersonic Inlets at Subcritical Conditions

Description: Memorandum presenting an investigation of the phenomenon of the starting of aerodynamic instability or buzz in supersonic inlets with external compression. The starting of the buzz has been related to the existence in the flow field of a velocity discontinuity across a vortex sheet which originates at a shock intersection. Results regarding the inlets without separation on the central body, inlets with separation on the central body, the regulation of entering volume flow at angles of attack, experimental performance of various inlets, and an application of the results are provided.
Date: January 26, 1951
Creator: Ferri, Antonio & Nucci, Louis M.
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of a New Type of Supersonic Inlet

Description: "A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is considered. A particular arrangement with fixed geometry having a central body with a circular annular intake is analyzed, and it is shown theoretically that this arrangement gives high pressure recovery for a large range of Mach number and mass flow and therefore is practical for use on supersonic airplanes and missiles. For some Mach numbers the drag coefficient for this type of inlet is larger than the drag coefficient for the type of inlet with supersonic compression entirely inside, but the pressure recovery is larger for all flight conditions" (p. 1).
Date: November 27, 1946
Creator: Ferri, Antonio & Nucci, Louis M.
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of a New Type of Supersonic Inlet

Description: "A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is considered a particular arrangement with fixed geometry having a central body with a circular annular intake is analyzed, and it is shown theoretically that this arrangement gives high pressure recovery for a large range of Mach number and mass flow and, therefore, is practical for use on supersonic airplanes and missiles. Experimental results confirming the theoretical analysis give pressure recoveries which vary from 95 percent for Mach number 1.33 to 86 percent for number 2.00. These results were originally presented in a classified document of the NACA in 1946" (p. 1).
Date: 1952
Creator: Ferri, Antonio & Nucci, Louis M.
Partner: UNT Libraries Government Documents Department

Theoretical and Experimental Analysis of Low-Drag Supersonic Inlets Having a Circular Cross Section and a Central Body at Mach Numbers of 3.30, 2.75, and 2.45

Description: Memorandum presenting a discussion of inlets with a circular cross section and a central body designed for high Mach numbers. The optimum proportion between external and internal supersonic compression is discussed in relation to the external drag and the maximum pressure recovery. Results and analysis regarding the maximum pressure recovery as a function of the cowling position parameter, the effect of the cone angle parameter on the maximum pressure recovery obtained, the highest pressure recovery obtained as a function of the central-body-diameter parameter, the maximum pressure recovery as a function of Mach number, and optical observations of the flow phenomena about the inlets are provided.
Date: November 10, 1948
Creator: Ferri, Antonio & Nucci, Louis M.
Partner: UNT Libraries Government Documents Department

Theoretical and Experimental Analysis of Low-Drag Supersonic Inlets Having a Circular Cross Section and a Central Body at Mach Numbers 3.30, 2.75, and 2.45

Description: Contains theoretical and experimental analysis of circular inlets having a central body at Mach numbers of 3.30, 2.75, and 2.45. The inlets have been designed in order to have low drag and high pressure recovery. The pressure recoveries obtained are of the same order of magnitude as those previously obtained by inlets having very large external drag.
Date: August 13, 1948
Creator: Ferri, Antonio & Nucci, Louis M.
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of a New Type of Supersonic Inlet

Description: "A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is considered. A particular arrangement with fixed geometry having a central body with a circular annular intake is analyzed, and it is shown theoretically that this arrangement gives high pressure recovery for a large range of Mach number and mass flow and therefore is practical for use on supersonic airplanes and missiles. For some Mach numbers the drag coefficient for this type of inlet is larger than the drag coefficient for the type of inlet with supersonic compression entirely inside, but the pressure recovery is larger for all flight conditions" (p. 1).
Date: April 1951
Creator: Ferri, Antonio & Nucci, Louis M.
Partner: UNT Libraries Government Documents Department