Rans COYOTE II S-6ES, Technical Manual

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020240cg msw 09/01/05
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GENERAL DESCRIPTION AND FLIGHT PROPERTIES
DESCRIPTION: The Coyote II is a high wing, tractor, mono plane with tricycle landing gear. It is strut braced
with aluminum tubing and welded 4130 steel construction. It has Dacron sailcloth pull on covers.
The design features a roll cage construction, an enclosed cabin when side doors are installed, shock absorbing
Tapered Steel type gear, steerable nosewheel, ailerons, and flaps.
FLIGHT PROPERTIES: The Coyote II flight properties are conventional in respect to general aviation aircraft
in the areas of control and response, with the exception of a greater speed decay rate due to its light but "large"
nature. This is typical of any lightweight plane, where little kinetic energy is to be had.
STALLS: Are preceded by an easily distinguishable buffet caused by the turbulence over the horizontal
stabilizer from the inboard wing stall. During this root stall, there is a sufficient lift and control to maintain flight.
Once the entire wing stalls the nose falls through very slightly and a high sink rate develops (approximately
1,000 to 1,500 fpm). The craft can be held wings level with the rudder.
NOTE: During this "falling leaf"
condition we assume full up elevator is applied.) The plane may take a couple of gentle 10 degree pitch ups if
the deep stall was entered from an exceptionally nose high attitude. Nonetheless, it will rapidly settle into a
slightly nose high mush until back pressure is released.
If, during a deep stall (falling leaf) the pilot's feet are removed from the rudder pedals, the Coyote II will begin to
dip each wing alternately until finally making a gentle spiral to the right or left. (
NOTE: This is not a spin! ) At
this point it could be argued that it is spinning. However, rotation is not through the plane's center mass.
Instead, it is as if it were riding down the sides of a vertical cylinder. Thus, I maintain it is a spiral. To further
support this, the spin properties are very conventional. Entry requires full deflection of elevator and rudder and
must be held in full deflection.
The spin's rotation is approximately 80 degrees nose down with rotation through the center mass, almost
through the aircraft centerline (10 degrees from it). Rotation speed is 3 seconds per turn. This is reached after
the second rotation and will not increase. Flight tests show no rotation increase even after 10 turn spins. Sink
rates average 1500 to 2000 fpm, with 200 to 400 feet lost per turn depending on density altitude.
This spiral and spin difference is easily recognized as well as controlled. Stall and spin testing in all
configurations has been done with no unusual characteristics revealed.
In conclusion, the Coyote II will spin only if fully stalled and ruddered. Recovery can be effected in 1/4 turn
using opposite control or in a 1/4 turn by neutralizing. Given the pronounced stall warning with quick recovery
rates from either stalls or spins, the Coyote II can be flown safely and predictable by the low time pilot.
As a result of the excellent stall warning and positive control ability, the Coyote II can be used as a S.T.O.L.
aircraft. With the 47 hp engine, take offs can be as short as 150 feet in no wind. Angle of climb can be 25
degrees to 35 degrees at 40 mph, 600 fpm and full flaps. (R.O.C. increase with retraction of flaps.) Expect
more performance with higher horsepower.
Testing has shown complete control and can be maintained during S.T.O.L. take offs and landings even when
"hanging it on the prop". In this mode an engine failure could result in a stall since airspeeds are in the 30 mph
range. Therefore, it should be used by the experienced and only when needed, for example, when landing on
an exceptionally short runway (800 feet with 50 foot or higher obstacles on each end).
TAKE-OFFS: Begin with a small amount of rudder to counteract the P factor. This diminishes once the speed
is up. Rotation generally occurs at 35 mph with climb out at 55 to 60 mph.
Cruise configurations will vary with loading, an average payload being 400 lbs. This average condition with the
47 hp engine yields a 3.75 gallons per hour fuel consumption at 78 mph and 6000 rpm.