CORRECTION OF THE EFFECT OF THE BOUNDARY LAYER ON THE FLOW IN NOZZLES WITH A BROKEN GENERATRIC (KORREKTIROVKA VLIYANIYA POGRANICHNOGO SLOYA NA TECHENIE V SOPLAKH S IZLOMOM OBRAZUYUSHCHEI),
Abstract
The larger the Mach number for which a supersonic nozzle is designed, the smaller the characteristic Reynolds number and, consequently, the larger the region of flow occupied by the boundary layer. For given diameters of the exhaust nozzle cross section and given flow parameters, a reduction of the boundary layer may be achieved by a reduction in nozzle length. Nozzles with a broken generatrix or nozzles with an angle point are of minimum length. U. G. Pirumov et al. (Chislennyye metody v gazovoy dinamike, Sbornik rabot, VTs MGU, no. 2, 1963) presented earlier a method for the design of axisymmetric nozzles with an angle point in the presence of equilibrium physicochemical transformation. The correction of the shape discussed in the present paper is supposed to secure a constant Mach number equal to the exit value M sub O in viscous flow along the axis of the nozzle (starting with a certain point). Following the known procedure of the boundary layer theory, the corrected shape is obtained from the original one by the shift in the direction of the outward normal through a distance equal to the thickness of the boundary layer displacement. Results are calculated for the M sub O value of 10. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 21, 1967
- Accession Number
- AD0674724
Entities
People
- L. V. Pchelkina
- V. K. Solodkin
Organizations
- National Air and Space Intelligence Center