An evaluation was made of the applicability and benefits of laminar flow control (LFC) technology to supersonic cruise airplanes. Ancillary objectives were to identify the technical issues critical to supersonic LFC application, and to determine how those issues can be addressed through flight and wind-tunnel testing. Vehicle types studied include a Mach 2.2 supersonic transport configuration, a Mach 4.0 transport, and two Mach 2-class fighter concepts. Laminar flow control methodologies developed for subsonic and transonic wing laminarization were extended and applied. No intractible aerodynamic problems were found in applying LFC to airplanes of the Mach 2 class, even ones of large size. Improvements of 12 to 17 percent in lift-drag ratios were found. Several key technical issues, such as contamination avoidance and excrescence criteria were identified. Recommendations are made for their resolution. A need for an inverse supersonic wing design methodology is indicated.
Feasibility and Benefits of Laminar Flow Control on Supersonic Cruise Airplanes
1989
121 pages
Report
Keine Angabe
Englisch
Aircraft , Boundary layer control , Fighter aircraft , Laminar flow , Supersonic cruise aircraft research , Supersonic transports , Aerodynamic configurations , Boundary layer stability , Feasibility analysis , Laminar boundary layer , Supersonic aircraft , Applications programs (Computers) , Flow coefficients , Leading edges , Lift drag ratio , Supersonic speed , Velocity distribution
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