Hypersonic Curved Compression Inlet and Its Inverse Design

Prof. Kunyuan Zhang is a Professor at the College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, China. He received his B.S. and M.S. degrees in Power Engineering from Nanjing Aeronautical Institute (now Nanjing University of Aeronautics and Astronautics) in 1965 and 1981, respectively, and he has been teaching at the same university since 1986. His research fields include hypersonic propulsion technology and internal flow dynamics.

Introduction.- Calculation and Analysis Method of Two Dimensional Curved Shock Wave Curved Compression Flow Field.- Forward Design of Two Dimensional Curved Shock Wave Curved Compression Surface.- Inverse Design of Compression Inlet with Specified Exit Aerodynamic Parameters.- Inverse Design of Curved Shock Wave Compression Surface on Basis of Specified Wall Aerodynamic Parameters.- Inverse Design of Axisymmetric Reference Flow Field on Basis of Specified Wall Aerodynamic Parameters.- Inverse Design and Experiment of Hypersonic Curved Shock Wave Compression Inlet.- Concept of Hypersonic Adaptive Variable Geometric Curved Compression Inlet.- Features and Drag Reduction Analysis of Drag in Hypersonic Inlet.- The Development of Curved Compression and Application Prospect.