نوع مقاله : مقاله علمی
عنوان مقاله English
نویسندگان English
Supersonic wind tunnels rely on convergent-divergent (CD) nozzles to accelerate air to a required test-section Mach number and pressure. Flow quality uniform Mach number distribution and minimal flow angle depends heavily on the divergent-section contour, which must be tailored to the target Mach number to avoid shock waves. This study presents a FORTRAN-based numerical code that applies the method of characteristics (MOC), combined with analytical transonic and centerline models, to design a shockless CD nozzle contour for an output Mach number of 3. The design was validated in ANSYS Fluent using a finite-volume, k-ε turbulence solver. Results show the nozzle produces a stable, uniform Mach number distribution with property deviations (temperature, pressure, density, velocity) below 0.25 across the outflow, confirming an effectively uniform, shock-free exit flow consistent with isentropic behavior. . . . . . . . . . . . . . . .. . . . . .
کلیدواژهها English
