The paper presents a design methodology for supersonic wing Sections with hybrid laminar flow control. The approach is based on coupled Euler/ boundary layer flow simulation and linear stability analysis for transition prediction. The investigations show that combinations of simple pressure distribution shapes can be used to optimize airfoils for maximum extent of laminar flow and hence minimum friction drag.
Laminar Design for Supersonic Civil Transport
2001
8 pages
Report
No indication
English
Aerodynamics , Aircraft , Fluid Mechanics , Laminar flow , Civil affairs , Supersonic transport aircraft , Linear systems , Control , Stability , Predictions , Shape , Airfoils , Germany , Hybrid systems , Transitions , Drag , Wings , Supersonic characteristics , Friction , German language , Pressure distribution , Component reports , Foreign reports
Laminar Design for Supersonic Civil Transport
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