Laminar flow wing for transonic cruise

In combination, an aircraft wing and fuselage, comprising

• a) said wing having maximum thickness extending spanwise, said maximum thickness decreasing from a primary wing zone proximate a fuselage indentation to a secondary wing zone at a selected distance from the fuselage centerline,
• b) said fuselage having indentations along the wing sides thereof, and lengthwise of the fuselage,
• c) said maximum thickness to chord ratio, t/c remaining less than about 3.5% from said secondary zone to the wing tip,
• c) the wing having a leading edge having blunted sharpness along substantially its entire length where the bluntness at each spanwise station is about ½% to 3% of the maximum airfoil thickness at said station, bluntness defined as h/t where h is the leading edge forward convexity diameter, and t is said maximum airfoil thickness.

In combination, an aircraft wing and fuselage, comprising

• a) said wing having camber at or near the wing leading edge which has blunted sharpness,
• b) the wing having leading edge low sweep angularity characterized in that crossflow instability is reduced to a subcritical level over the majority of the wing,
• c) the wing having thickness to chord ratio less than about 3% as a spanwise average, and
• d) said fuselage having indentations along the wing side thereof, and lengthwise of the fuselage, characterized in that fuselage and propulsion unit area ruling is defined,
• e) said wing leading edge having blunted sharpness along substantially its entire length where the bluntness at each spanwise station is about ½% to 3% of the maximum airfoil thickness at said station bluntness defined as h/t where h is the leading edge forward convexity diameter, and t is said maximum airfoil thickness.