Mini-IMP Aircraft Company


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The wings of the Mini-IMP incorporate a constant chord planform which together with slight aerodynamic twist results in any stalling action progressing outward from the center section with the wing tips stalling last.  The conical camber wing tips not only further assist in this regard, but they add significantly to the lateral and longitudinal stability, as well as impart a semi-end plate effect which tends to increase the effective span of the wing.  The aileron control system employs a 3:1 differential for the aileron displacement, and this too reduces any tendency for the inside wing to stall in a turn or during recovery from a turn or unusual attitude.  The Mini-IMP employs a NASA-developed derivative of the widely publicized GA (W)-1 airfoil in order to obtain higher lift and improved performance.  The GA(PC)-1 airfoil employs a system whereby the trailing edge of the wing can be varied by an infinitely adjustable control from a 10 degree depression of BOTH trailing edge full span surfaces to a 10 degree “reflexed” UP position.  This control of the trailing edge “flaperons” permits the pilot to vary the lift and drag and pitching moment of the wing.  The hand control for moving the flaperons is located adjacent to the throttle on the left side of the cockpit and gives the pilot a third “flight control” which permits the pilot to “play” the wing as desired for faster takeoff, glide path control, etc.  The effect is much like “spoilers” which are used on modern jets and sailplanes.  This feature, together with the very simple piano hinge type mechanical attachment of the flaperons, greatly simplifies wing construction.  The wings are flush blind riveted with butt-jointed wraparound skins.  This gives the wings extremely smooth contours, which also add to flight performance.

The wing spars are bolted together employing standard 2024 aluminum bar stock for the caps and sheet metal shear webs.  The center section of the wing is sealed with PRO-SEALä and forms the 12 ½ gallon fuel tank as an integral part of the structure.  A simple sight gage is used on the prototype for indicating fuel level and a flush filler neck is installed on top of the wing with a locking gas cap.  The prototype was originally built with a one-piece wing which can be removed from the fuselage by removing two bolts, disconnecting the “quick-disconnect” fuel line fittings and the positive lock aileron control system.  A folding wing was later installed on the prototype.  The simplicity of the folding mechanism, and the small building space required for the folding wing panels make this design far more practical than the original long one-piece wing which (while simple) required a very long building area for its construction.  The one-piece wing also proved to be somewhat unwieldy to handle, install, and trailer.  The folding wing system overcomes all of these problems and is the recommended arrangement.  Drawings for the folding wing are a part of the drawing set.  The drawing set also shows the one-piece wing if desired.  With the 3-piece wing, the center section is left attached to the fuselage for towing the aircraft on a simple trailer.  The center section of the wing is covered with a single molded piece of fiberglass, which fairs the fuselage into the wing, tail and canopy.  The foldable wing arrangement uses tapered wing attach pins and a fold fitting at the rear spar to assure positive, easy alignment of the fittings when spreading the wings for flying.


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