Wing and reduced airspeed system for jet aircraft

Claim 2

In a linearly tapered wing having an NACA 64A-109 type airfoil section with a root chord of 100 percent length and a tip chord length as a fraction of the root chord length to define a taper ratio, and upper and lower surfaces defined as fractions of a chord length, the improvement comprising: a contoured leading edge having a substantially constant radius selected from the range of about 0.0070 to about 0.0129 of the tip chord divided by the taper ratio, the leading edge radius substantially tangent with the upper surface of the wing and the leading edge faired into the lower surface of the wing within the range of about 6 to about 15 percent of a chord.

Claim 3

The wing as claimed in claim 1 wherein the wing has a taper ratio in the range of about 0.40 to about 0.60.

Claim 4

The wing as claimed in claim 1 wherein the leading edge radius is substantially 0.01247 of the tip chord divided by the taper ratio substantially throughout the span of the wing.

Claim 5

The wing as claimed in claim 1 wherein the wing has a quarter chord sweep of substantially 13°.

Claim 6

In a linearly tapered wing with a tip chord length as a fraction of a root chord to define a taper ratio, the wing having an NACA 64A-109 type wing section and a quarter chord sweep of about 13 degrees, the improvement comprising a leading edge having a radius characterized by the formula: ##EQU1## where R L .E. is the leading edge radius as a fraction of the root chord length, K is a constant selected of the range of about 0.0070 to of about 0.0129, C t is the tip chord length as a fraction of root chord length, and T r is the taper ratio of the range of about 0.4 to about .6.

Claim 7

In a linearly tapered wing with a tip chord length as a fraction of a root chord to define a taper ratio, the wing having an NACA 64A-109 type wing section and a quarter chord sweep of about 13 degrees, the improvement comprising a leading edge having a radius characterized by the formula: ##EQU1## where R L .E. is the leading edge radius as a fraction of the root chord length, K is a constant selected of the range of about 0.0070 to of about 0.0129, C t is the tip chord length as a fraction of root chord length, and T r is the taper ratio of the range of about 0.4 to about .6.

Claim 8

The wing as claimed in claim 5 wherein the constant K is substantially 0.01247 and T r is substantially 0.507.

Claim 9

In an aircraft of the Gates Learjet type having a tapered wing substantially characterized by an NACA 64A-109 airfoil section throughout the wing span, an improved wing leading edge characterized by a constant leading edge radius substantially through the wing span and selected from the range of about 1.25 to about 1.40 inches, the constant leading edge radius defining a substantially blunt leading edge with increased camber and droop that increses from wing root to wing tip.

Claim 10

In an aircraft of the Gates Learjet type having a tapered wing substantially characterized by an NACA 64A-109 airfoil section throughout the wing span, an improved wing leading edge characterized by a constant leading edge radius substantially through the wing span and selected from the range of about 1.25 to about 1.40 inches, the constant leading edge radius defining a substantially blunt leading edge with increased camber and droop that increses from wing root to wing tip.

Claim 11

The aircraft combination as claimed in claim 7 wherein the leading edge radius is substantially consistently 1.35 inches.

Claim 12

In an aircraft of the Gates Learjet type (FAA Certification A10CE) characterized by a tapered, swept wing substantially as defined by NACA 64A-109 airfoil except for the leading edge forward of about 15% of the NACA defined chord line; a T-tail with elevators interconnected to and activateable by a stick shaker/pusher system; and fuel tanks mounted at the tips of the wing, the combination comprising: a leading edge interconnected to the wing generally forward of about the 15 percent NACA chord line, the leading edge characterized by a constant radius substantially across the wing span, the radius of the range of about 1.25 to 1.40 inches that defines a generally blunt, drooped leading edge near the wing tip that increases in camber and droop from the wing root to wing tip; and a rate of change of angle of attack sensor interconnected to and with means for activating the stick shaker/pusher system.

Claim 13

In an aircraft of the Gates Learjet type (FAA Certification A10CE) characterized by a tapered, swept wing substantially as defined by NACA 64A-109 airfoil except for the leading edge forward of about 15% of the NACA defined chord line; a T-tail with elevators interconnected to and activateable by a stick shaker/pusher system; and fuel tanks mounted at the tips of the wing, the combination comprising: a leading edge interconnected to the wing generally forward of about the 15 percent NACA chord line, the leading edge characterized by a constant radius substantially across the wing span, the radius of the range of about 1.25 to 1.40 inches that defines a generally blunt, drooped leading edge near the wing tip that increases in camber and droop from the wing root to wing tip; and a rate of change of angle of attack sensor interconnected to and with means for activating the stick shaker/pusher system.

Claim 14

The aircraft as claimed in claim 9 and further including two strakes, which are disposed between and attached to portions of the leading edge of the wing tips and sides of the tip tanks.

Claim 15

The aircraft as claimed in claim 10 wherein the wing has an aspect ratio of about 5.02, a taper ratio of about 0.507, a quarter chord sweep of about 13° and a dihedral angle of about 2.5°.

Claim 16

In a wing having an NACA 64A-109 airfoil section, a taper ratio between the root chord and tip chord of about 0.507, a quarter chord sweep of about 13°, the improvement comprising: root section leading edge ordinates forward of a 15 percent chord characterized by: ______________________________________ Upper Surface Lower Surface Station Ordinate Station Ordinate ______________________________________ - .037 - .265 - .037 - .265 .324 .607 1.247 .650 .857 radius 1.950 1.452 1.213 1.512 3.251 1.865 Straight 4.551 2.182 Line 5.851 2.467 From 7.44 2.77 Tangent 9.94 3.18 Point 14.94 3.82 15.00 - 3.029 ______________________________________ tip section leading edge ordinates forward of a 15 percent chord characterized by: ______________________________________ Upper Surface Lower Surface Station Ordinate Station Ordinate ______________________________________ - 2.105 -1.717 - 2.105 - 1.717 - 1.580 - .350 2.212 - 1.154 .104 radius .546 .942 .107 -3.929 2.247 1.547 Straight 3.948 2.019 Line 5.649 2.418 From 7.44 2.77 Tangent 9.94 3.18 Point 14.94 3.82 15.00 -3.029 ______________________________________ and a constant leading edge radius between the root and tip sections of about 1.35 inches.

Claim 17

In a wing having an NACA 64A-109 airfoil section, a taper ratio between the root chord and tip chord of about 0.507, a quarter chord sweep of about 13°, the improvement comprising: root section leading edge ordinates forward of a 15 percent chord characterized by: ______________________________________ Upper Surface Lower Surface Station Ordinate Station Ordinate ______________________________________ - .037 - .265 - .037 - .265 .324 .607 1.247 .650 .857 radius 1.950 1.452 1.213 1.512 3.251 1.865 Straight 4.551 2.182 Line 5.851 2.467 From 7.44 2.77 Tangent 9.94 3.18 Point 14.94 3.82 15.00 - 3.029 ______________________________________ tip section leading edge ordinates forward of a 15 percent chord characterized by: ______________________________________ Upper Surface Lower Surface Station Ordinate Station Ordinate ______________________________________ - 2.105 -1.717 - 2.105 - 1.717 - 1.580 - .350 2.212 - 1.154 .104 radius .546 .942 .107 -3.929 2.247 1.547 Straight 3.948 2.019 Line 5.649 2.418 From 7.44 2.77 Tangent 9.94 3.18 Point 14.94 3.82 15.00 -3.029 ______________________________________ and a constant leading edge radius between the root and tip sections of about 1.35 inches.

Claim 18

In a linearly tapered wing of the thin, high speed type having an airfoil section with a root cord of 100% length and a tip cord length as a fraction of the root cord length to define a taper ratio, and upper and lower surfaces defined as fractions of a cord length, the improvement comprising: a contoured leading edge having a substantially constant radius dimension selected from the range of about 0.0070 to about 0.0129 of the tip cord divided by the taper ratio, the leading edge radius substantially tangent with the upper surface of the wing and the leading edge fared into the lower surface of the wing within a range of about 6 to about 15 percent of a cord.

Claim 19

In a linearly tapered wing of the thin, high speed type having an airfoil section with a root cord of 100% length and a tip cord length as a fraction of the root cord length to define a taper ratio, and upper and lower surfaces defined as fractions of a cord length, the improvement comprising: a contoured leading edge having a substantially constant radius dimension selected from the range of about 0.0070 to about 0.0129 of the tip cord divided by the taper ratio, the leading edge radius substantially tangent with the upper surface of the wing and the leading edge fared into the lower surface of the wing within a range of about 6 to about 15 percent of a cord.