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     OR 4 ADULTS


2,000 FT PER MIN


1,100 NM


90 - 100 GALLONS


3,200-3,440 LBS


-185-205 KTAS non  turbo
-230-250 KTAS with turbo


The Velocity V-Twin was designed to provide a safe and efficient transportation aircraft especially for those who fly at night, over mountains, over large bodies of water, serious IFR and those who just want the redundancy of a second engine to get them home or to an airport in the event of an engine failure. One of the design goals was to provide a twin engine aircraft that does NOT have the “stall/spin” problems associated with most twin engine aircraft. Think of it this way: Should you lose one engine of a conventional twin during the most critical departure point when the airspeed is low and in a climb attitude, panic will set in and often the pilot will not initiate the essential elements of an engine out procedure. He now finds that it takes full rudder to keep the airplane from yawing, airspeed is decaying and a turn back to the runway can result in the lowered wing to stall. Not much different than most airplanes where you use full rudder and slow the airplane down to a stall resulting in a spin. Key decisions used in a twin are: “identify,” “verify,” and “secure.” Identify the engine that failed by using the dead foot, dead engine terminology, verify by retarding the throttle that represents the dead engine and then secure the dead engine by feathering the propeller and shutting off the fuel to that engine. Struggling all at the same time to maintain a safe flying speed and keeping the airplane from crashing into the trees or other obstacles on the departure path.

How is the V-Twin Different?

Here is what is different in our V-Twin. The canard design results in the canard stalling before the main wing can reach a critical stall angle. The nose will bob up and down but the wing continues to fly. The end result is that IF you can’t stall the main wing, you can’t spin. This gives the pilot time to identify, verify and secure even if his air speed decays to the point where the canard does the bob up and down thing. Our power to weight is higher than most conventional twins thus giving us a better rate of climb should an engine fail.

V-Twin Specifications

Length Overall



7' 10"

Wheel Base


Track Width




Canard Span


Main Wing Area

132.5 Sq Ft

Canard Wing Area

22.8 Sq Ft

Total Wing Area

155.3 Sq Ft

Fuel Capacity

95 Gallons

Design Load Factors


Tested Airframe Load

+6 G-Load

Cabin W/L/H

47.5" x 94" x 43.5"


4 to 5

Take Off Distance

1500 ft

Rate of Climb

2000 fpm

Landing Distance

1500 ft


200 kias


25000 ft

Minimum Speed

74 kts

Landing Speed

85 kts

V-Twin ENGINE Specifications


Lycoming IO 320
Lycoming IO 360
Titan IO 370
Deltahawk Diesel


160 hp
180 hp
190 hp
180 hp
220 hp

Empty Weight

2000 lbs
2020 lbs
2020 lbs
2240 lbs.
2100 lbs.

Gross Weight

3200 lbs
3400 lbs
3400 lbs
3440 lbs.
3400 lbs.

Useful Load

1200 lbs
1380 lbs
1380 lbs
1200 lbs.
1300 lbs.

Wing Loading at Gross

19 psf
21 psf
21 psf
21 psf
21 psf

Cruise Speed at 75%

185 ktas*
200 ktas*
205 ktas*
250+ ktas*
230+ ktas*

Fuel Burn  @ 65%

13 gph total
16 gph tota
18 gph total
12 gph total
19 gph total

Range at 65%

1400 NM
1150 NM
1150 NM
1900 NM
1150 NM

*Expect a 5-7% knot decrease in cruise speed with fixed gear variant

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