Methods and systems for controlling lower surface shocks
AssigneeThe Boeing Company
InventorDavid R. Bogue
Life of this patent
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Abstract
Methods and systems for controlling shocks on airfoil lower surfaces are disclosed. An airfoil in accordance with one embodiment of the invention includes an upper surface portion having an upper surface positioned to face generally upwardly during the level flight, and a lower surface portion having a leading edge region, a trailing edge region and a lower surface positioned to face generally downwardly during level flight. A shock control protrusion extends away from the lower surface and is positioned to generate a shock extending away from the lower surface at a least one flight condition.
Claims29
A transonic airfoil, comprising:
- an upper surface portion having an upper surface positioned to face generally upwardly during level flight;
- a lower surface portion having a leading edge region and a trailing edge region, the lower surface portion further having a lower surface positioned to face generally downwardly during level flight;
- and
- a shock control protrusion extending from the lower surface and having a generally downwardly and forward facing surface with an aft fairing generally smoothly blended with the lower surface, the shock control protrusion being positioned to generate a shock extending away from the lower surface at level flight Mach numbers of at least 0.80.
A transonic airfoil, comprising:
- an upper surface portion having an upper surface positioned to face generally upwardly during level flight;
- a lower surface portion having a leading edge region and a trailing edge region, the lower surface portion further having a lower surface positioned to face generally downwardly during level flight;
- and
- a plurality of shock control protrusions extending from the lower surface and having a generally downwardly facing surface with an aft fairing generally smoothly blended with the lower surface, with individual shock control protrusions being positioned to generate a shock extending away from the lower surface at level flight Mach numbers of at least 0.80.
A transonic aircraft, comprising:
- a fuselage;
- and
- an airfoil coupled to the fuselage, the airfoil including:
- an upper surface portion having an upper surface positioned to face generally upwardly during level flight;
- a lower surface portion having a leading edge region and a trailing edge region, the lower surface portion further having a lower surface positioned to face generally downwardly during level flight;
- and
- a shock control protrusion extending from the lower surface and having a generally downwardly and forward facing surface with an aft fairing generally smoothly blended with the lower surface, the shock control protrusion being positioned to generate a shock extending away from the lower surface at level flight Mach numbers of at least 0.80.
Dependencies are inferred from the claim text.