Stalling aerodynamics of the Cessna models 150 and 152 series aircraft

Claim 1

An improvement to the stalling aerodynamics and stall characteristics of Cessna 150/152 series aircraft having a fuselage and two wings having a span, leading edges, wing tips and wing roots, the leading edge of each wing having a centerline, wherein the improvement comprises: the fixed securement of an immovable, non-pivoting, rigid strip, on substantially the centerline of the leading edge of each wing, on that portion of each said wing substantially adjacent to each wing root to passively trigger the separation of air flow against the wing at the wing root; said strip of unchanging triangular shape having two termini defining a length thereinbetween, two substantially even raised surfaces, a contour surface and a plurality of recesses having securement orifices; said substantially even raised surfaces of said strip intersecting at a permanently determined raised surface junction, said raised surface junction having an angle substantially from about 80° to about 100°; and said contour surface intersecting both said raised surfaces of said strip at raised-contour surface junctions having an angle substantially from about 35° to about 55°, said contour surface and said raised-contour surface junctions fixedly secured to a small chordwise portion of said leading edge of said wing about said centerline, said strip immovably extending the leading edge of the wing into the airflow over a portion of the wing within four feet of the wing root, whereby said immovable, non-pivoting securement of said strip on substantially the centerline of the narrow chordwise portion of each said wing at a distance within four feet of said wing root minimizes the incidence of unintentional roll into spin entry by forcing the wing root to stall prior to the wing tip without affecting the handling properties and the normal aerodynamic properties of the aircraft at a speed above stall speed for the aircraft.

Claim 7

A method to minimize the incidence of unintentional roll into spin entry resulting from stalled conditions over the entire surface of the wing of Cessna 150/152 series aircraft having wing roots and wing tips, comprising the steps of: identifying the location above the stagnation point at substantially the centerline of the leading edge of each wing of the aircraft at the desired stalling angle of attack; and fixedly securing an immovable, non-pivoting, rigid strip to substantially the centerline of said leading edge on a portion of each said wing substantially adjacent to each wing root, said strip of unchanging triangular shape having two termini, two substantially even raised surfaces, a contour surface, and a plurality of recesses having securement orifices; two said substantially even raised surfaces of said strip intersecting at a permanently determined raised junction, said raised surface junction having an angle substantially from about 80° to about 100°; and said contour surface intersecting both said raised surfaces of said strip at raised-contour surface junctions having an angle substantially from about 35° to about 55°, said contour surface and said raised-contour surface junctions fixedly secured to a small chordwise portion of said leading edge of said wing about said centerline, said strip immovably extending the leading edge of the wing into the air flow over a portion of the wing within four feet of the wing root, whereby said immovable, non-pivoting securement of said strip on substantially the centerline of the narrow chordwise portion of each said wing at a distance within four feet of said wing root minimizes the incidence of unintentional roll into spin entry by forcing the wing root to stall prior to the wing tip without affecting the handling and the normal aerodynamic properties of the aircraft at a speed above stall speed for the aircraft.

Claim 8

A method to minimize the incidence of unintentional roll into spin entry resulting from stalled conditions over the entire surface of the wing of Cessna 150/152 series aircraft having wing roots and wing tips, comprising the steps of: identifying the location above the stagnation point at substantially the centerline of the leading edge of each wing of the aircraft at the desired stalling angle of attack; and fixedly securing an immovable, non-pivoting, rigid strip to substantially the centerline of said leading edge on a portion of each said wing substantially adjacent to each wing root, said strip of unchanging triangular shape having two termini, two substantially even raised surfaces, a contour surface, and a plurality of recesses having securement orifices; two said substantially even raised surfaces of said strip intersecting at a permanently determined raised junction, said raised surface junction having an angle substantially from about 80° to about 100°; and said contour surface intersecting both said raised surfaces of said strip at raised-contour surface junctions having an angle substantially from about 35° to about 55°, said contour surface and said raised-contour surface junctions fixedly secured to a small chordwise portion of said leading edge of said wing about said centerline, said strip immovably extending the leading edge of the wing into the air flow over a portion of the wing within four feet of the wing root, whereby said immovable, non-pivoting securement of said strip on substantially the centerline of the narrow chordwise portion of each said wing at a distance within four feet of said wing root minimizes the incidence of unintentional roll into spin entry by forcing the wing root to stall prior to the wing tip without affecting the handling and the normal aerodynamic properties of the aircraft at a speed above stall speed for the aircraft.