What question did this study set out to answer?

This research aims to evaluate how surface roughness affects the aerodynamic performance of transonic axial compressors at different altitudes.

February 25, 2026

Influence of Surface Roughness on the Aerodynamic Performances of a Transonic Axial Compressor under Varying Fighter Operational Altitudes

Key Points

This research aims to evaluate how surface roughness affects the aerodynamic performance of transonic axial compressors at different altitudes.
Conducted a three-dimensional Reynolds-averaged Navier-Stokes (RANS) simulation using NASA Rotor 67.
Employed ANSYS CFX for computational fluid dynamics (CFD) analysis.
Used the Shear Stress Transport (SST) Gamma-Theta transition turbulence model for boundary layer behavior.
Introduced a Reynolds Number Index (RNI) to simulate flight conditions at various altitudes.
Modeled and compared three blade configurations with different surface roughness levels.
Found significant changes in boundary layer characteristics based on surface roughness and altitude conditions.
Observed variations in pressure ratio and surge margin related to different surface roughness levels.
Identified changes in boundary layer thickness, flow separation, and shock wave structure due to surface roughness.

Abstract

This study investigates the aerodynamic effects of blade surface roughness under varying altitude conditions relevant to high-altitude operation of military aircraft engines. To analyze the flow behavior and performance variations induced by surface roughness, a three-dimensional Reynolds-averaged Navier-Stokes (RANS) simulation was conducted using NASA Rotor 67 as the base geometry. The commercial CFD software ANSYS CFX was employed, and grid independence was ensured through the Grid Convergence Index (GCI) method. To capture the transition-sensitive boundary layer behavior, the Shear Stress Transport (SST) Gamma-Theta transition turbulence model was applied. In order to represent flight conditions at various altitudes, a Reynolds Number Index (RNI) ranging from 0.3 to 1.0 was introduced to define the inlet flow regime. Three blade configurations with different surface roughness levels were modeled and compared. The analysis focused on changes in boundary layer characteristics, pressure ratio, and surge margin, highlighting the role of surface roughness under varying RNI conditions. Specifically, the boundary layer thickness, flow separation and reattachment locations, and the structure of shock waves were found to change depending on the surface roughness and RNI. Consequently, these changes led to variations in the aerodynamic performance and flow stability of the compressor.

AI에게 질문

Bookmark