Accession Number : ADA382078

Title :   Preliminary Investigation of a New Type of Supersonic Inlet

Descriptive Note : Technical note

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER

Personal Author(s) : Ferri, Antonio ; Nucci, Louis M.

PDF Url : ADA382078

Report Date : APR 1951

Pagination or Media Count : 43

Abstract : 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. The differences in drag can be eliminated for the design Mach number. Experimental results confirm the results of the theoretical analysis and show that pressure recoveries of 9% percent for Mach numbers of 1.33 and l.52, 92 percent for a Mach number of l.72, and 86 percent for a Mach number of 2.10 are possible with the configurations considered. If the mass flow decreases, the total drag coefficient increases gradually and the pressure recovery does not change appreciably. The results of this work were first presented in a classified document issued in l946.

Descriptors :   *DECELERATION, RECOVERY, HIGH PRESSURE, MASS FLOW, SUPERSONIC INLETS.

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE