The aerodynamic design of a supersonic oblique flying wing is strongly influenced by the requirement that passengers must be accommodated inside the wing. It was revealed that thick oblique wings of very high sweep angle can be efficient at supersonic speeds when transonic normal Mach numbers are allowed on the upper surface of the wing. The goals were motivated by the ability to design a maximum thickness, minimum size oblique flying wing. A 2-D Navier-Stokes solver was used to design airfoils up to 16 percent thickness with specified lift, drag and pitching moment. A new method was developed to calculate the required pressure distribution on the wing based on the airfoil loading, normal Mach number distribution and theoretical knowledge of the minimum drag of oblique configurations at supersonic speeds. The wing mean surface for this pressure distribution was calculated using an inverse potential flow solver. The lift to drag ratio of this wing was significantly higher than that of a comparable delta wing for cruise speeds up to Mach 2.
Aerodynamic Design of the Oblique Flying Wing Supersonic Transport
1990
69 pages
Report
Keine Angabe
Englisch
Aircraft , Aerodynamics , Aircraft design , Computational fluid dynamics , Delta wings , Oblique wings , Supersonic transports , Wing profiles , Aerodynamic loads , Lift drag ratio , Mach number , Mathematical models , Minimum drag , Navier-stokes equation , Pitching moments , Potential flow , Pressure distribution , Sweep angle