Botmite Details & photos:

New-Wings  Botmite 1.1

72 inch by 12 inch chord wings

   Increased CL. to 1.6 max without Flaps. Maintained low CD ~.01, increased wing stiffness and strength.  Wings now quickly interchangable, greatly reduced wing flex.. Cut turning radius at increased flight dynamics. Lowered piloting skills required to fly airplane. Improved Lift by increasing wing area by 59%. Steep Climbs now possible. Flight time enhanced.  Increased flying speed envelope. Increased weight capacity while lowering landing and stall speeds. Extended range and lowered risk of crashing. Improved stability in windy flying conditions.  Lowered Aspect Ratio and CM (moment) of wing - both work to stabilize flight characteristics of the aircraft. . 

   A Clark-Y or E-205 (Eppler) airfoil selection forms the external shape of the wings. Internally, each wing is undergoing calcs to determine the material composition and structure.

   See the pdf file for preliminary information.

                                   Basic 2 dimensional analysis of Airfoil
  Symbols: p = atmospheric pressure   V = velocity of aircraft   C = Area of Wing
                   l = lift, d = drag, m = pitching moment (nose-tail up-down) 
   Note: iteration of Angle of Attack (alpha), Camber and Wing Thickness directly changes
   these coefficients.   Aspect Ratio (wingspan to chord ratio) effects Wing Efficiency
   and Lift performance. Smaller  airfoil moment usually means smaller tail, less bouncy.
   The Re (Reynolds Number - typically Velocity and aircraft size or scale) effects lift,
   drag, moment and performance factors.
                 Cd = coefficient of drag, Cl = coefficient of lift, Cm = coefficient of moment
 

                       In Development
  Flying Weight: 9 pounds or 144 ounces
  Wing Area: 6 square feet or 864 sq, inches
  Wing Span: 6 feet or 72 inches
  Wing Chord: 1 foot or 12 inches
  Wing Loading: 24 oz./sq.ft. or 1.5 lb/sq,ft
  Cubic Wing Loading: 9.8 oz./cubic foot
  Wing Covering: .62 grams/square inch
  Wing Geometry: rectangle, no taper
  Aspect Ratio: 6
  Tail-Wing Area Ratio: 0.09
  Aircraft Loads: +6 g, -4 g
  Max Rate of Climb: 3,300 fpm
  Max Roll Helix: 2 turns per second
 

 

             Original Design
  Flying Weight: 7.5 pounds or 120 oz.
  Wing Area: 3.54 sq. ft. or 510 sq. in.
  Wing Span: 8 feet or 96 inches
  Wing Root Chord: ~ 9 inches
  Wing Loading: 38.4 oz./sq.ft.
  Cubic Wing Loading:
9.85 oz/cubic foot
   Wing Covering:   grams/square inch
   Wing Geometry: sailplane, tapered

   Aspect Ratio: 12
   Tail-Wing Area Ratio: 0.20
   Aircraft Loads: +2 g, -2 g
   Max Rate of Climb:
   Max Roll Helix: 1 turn per second
  

 

See wings page for further updates on new wing.

   Basic comparison between original E-374 (mod) wing and in development foam core wing (white styrafoam) airfoil inside the block. Both new Clark-Y and E-205 airfoils have same planform dimensions - fuselage attachment requires modification.

   First wood template jigsaw cut from 1/4 inch plywood veneer, then sanded. This wood marking template sets the internal perimeter to mark balsa or other  plate for use as internal airfoil ribs. No holes drilled to align internal structures and no access openings or reinforcements cut on this template.

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