Accession Number : AD0466580


Title :   IMPROVED METHODS FOR DETERMINING SECOND-THROAT DIFFUSER PERFORMANCE OF ZERO-SECONDARY-FLOW EJECTOR SYSTEMS


Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN


Personal Author(s) : German, R C ; Panesci, J H


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/466580.pdf


Report Date : Jul 1965


Pagination or Media Count : 68


Abstract : Improved methods are presented for estimating the required starting pressure ratio of a given axisymmetric second-throat, ejector-diffuser system used in rocket altitude simulation. The improved theory involves a more accurate technique for determining ramp pressure. The new technique utilizes the flow field approaching the second throat along with two-dimensional oblique shock relations and the conservation equations to determine the conditions at the throat entrance. The results are applied to second-throat diffusers with throat lengths varying from 0.2 to 8.1 throat diameters and to second throats with a center-body located at various positions.


Descriptors :   *ALTITUDE CHAMBERS , *DIFFUSERS , *EXHAUST NOZZLES , ANNULAR NOZZLES , EQUATIONS , EXPERIMENTAL DATA , GRAPHICS , HIGH ALTITUDE , JET PUMPS , MATHEMATICAL ANALYSIS , MODEL TESTS , NOZZLE CLUSTERS , NOZZLE GAS FLOW , PERFORMANCE(ENGINEERING) , PLUG NOZZLES , PRESSURE , ROCKET NOZZLES , SHOCK WAVES , SIMULATION , STARTING , TABLES(DATA) , TEST EQUIPMENT , TEST FACILITIES , THEORY


Subject Categories : Machinery and Tools
      Test Facilities, Equipment and Methods
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE