DIAGRAM FOR OPTIMUM DESIGN OF A SYSTEM OF SHOCKS IN AXIALLY SYMMETRICAL SUPERSONIC DIFFUSERS WITH EXTERNAL COMPRESSION,

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Abstract:

The article proposes a diagram for designing axisymmetrical supersonic multi-shock diffusers which considerably decrease the pressure losses during the stagnation of supersonic air flows. Such a diagram can be used for selecting the optimum geometry of the inner body of a diffuser and for determining the flow parameters. The diagram was constructed for a system consisting of a number of oblique shocks followed by a normal shock. The diagram gives the M number behind a shock and the angles of the shock front and the flow deflection as a function of the M number in front of the shock. Thus, by decreasing after each shock the number of remaining oblique shocks, the overall flow parameters and the geometry of the inner body of a diffuser can be determined. Author

Author(s):
Pudoveev, A. P.
Author Organization(s):
FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
Supplementary Note:
Unedited rough draft trans. of Izvestiya Vysshikh Uchebnykh Zavedenii. Aviatsionnaya Tekhnika (USSR) n2 p151-3 1966, tr. by L. Marokus.
Annotation:
Diagram for optimum design of a system of shocks in axially symmetrical supersonic diffusers with external compression--Translation.
Pagination:
0009

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
FTD-HT-23-682-67
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*SUPERSONIC DIFFUSERS, AXISYMMETRIC FLOW, OPTIMIZATION, SHOCK WAVES, STAGNATION POINT, MACH NUMBER, USSR
Field(s)/Group(s):
Aerodynamics, Fluid Mechanics
Keyword(s):
TRANSLATIONS
Report Date:
1967 Jul 18