TURBULENT NONISOTHERMAL FLOW OF A VISCOUS COMPRESSIBLE GAS IN THE INITIAL SEGMENTS OF AXISYMMETRIC AND PLANE DIVERGING CHANNELS WITH A ZERO PRESSURE GRADIENT (TURBULENTNOE NEIZOTERMICHESKOE TECHENIE VYAZKOGO SZHIMAEMOGO GAZA NACHALNYKH UCHASTKAKH OSESIMMETRICHNYKH I PLOSKIKH RASSHIRYAYUSHCHIKHKSYA KANALOV S NULEVYM GRADIENTOM DAVLENIYA),
Abstract
In the inlet section of a channel the velocity, the temperature, the Mach number, and other flow parameters are distributed uniformly over the channel cross section. As the distance from the inlet section increases, a boundary layer arises due to the effect of viscous forces on the walls of the channel and there is an isoentropic flow core at parts of the section located nearer to the axis. It is assumed also that heat transfer affects the velocity and temperature distributions only within the boundary layer. It follows that the velocity, temperature, Mach number, and other flow parameters remain constant across the channel in the flow core. Flow in the boundary layer is assumed to be turbulent. The article proposes to solve the given problem taking into account the effect of the transverse curvature of the surface on the axisymmetrical turbulent boundary layer. There follows an extended mathematical development based on the foregoing assumptions. Results of the calculations are exhibited in the form of curves showing the change in the local coefficient of friction resistance along the axis, the length of the initial section of the channel under various conditions, and change in the local heat transfer coefficient along the axis. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 21, 1967
- Accession Number
- AD0671743
Entities
People
- A. S. Ginevskii
- E. E. Solodkin
Organizations
- National Air and Space Intelligence Center