Products

PUL 9

THE FIRST TEST AIRPLANE
The PUL 9 flying wing was created from Dr. Horten's calculations and it proved the concept. In early 1990 construction began in Hirschberg, Germany. In Bologna, Italy Nike Aeronautica completed the final assemly. Test flights at the company owned airfield began in late 1990. Horten's theories were proven and the test pilots were very impressed with its well behaved flying characteristics and ease of control. Developement of the single seat flying wing was discontinued after market research showed that the public preferred a two seat aircraft.

Technical data for the PUL 9

Wing Span 9 m (29.53 ft) Overall Length 3.41 m (11.19 ft) Height 1.42 m (4,66 ft) Wing Area 11.2 m² (120.5 ft²) Empty Weight 172 kg (379 lbs) Gross Weight 250 kg (551 lbs) Useful Load 98 kg (216 lbs) Fuel Capacity 30 ltr (8 gals) Seating 1 Engine Rotax 582 Propeller Fixed-Pitch Flaps None Landing Gear Fixed Power (max.) 54 PS (54 HP) Cruising Speed 160 km/h (86 kts) Maximum Speed 185 km/h (100 kts) Minimum Speed 50 km/h (27 kts) Range at 75% power 430 km (232 nm)

PUL 10

THE FIRST TWOSEATER
The success of the PUL 9 flight tests and the demand of a two seat aircraft led to the developement of the PUL 10. Under the supervision of Dr. Horten a full scale mockup was prepared in Argentina. In Germany in 1992 the molds for the PUL 10 were built and construction of the first prototype began. The final assembly and the first test flights were done in Bologna, Italy at the NIKE Aeronautica company airfield.

ATTRACTING ATTENTION
In the course of its test flights the PUL 10 attracted the attention of the national and international press. We were inundated with requests for information about this aircraft. We decided to build another PUL 10, this one with retractable landing gear.

Test flights began in Italy in 1994 and were continued on Sarrebourg Airfield in France.

ACCIDENT DURING FLIGHT TESTING
In 1995 a flight to test the stall characteristics with a centre of gravity too far aft forced us to recover control by firing an emergency parachute. That saved the pilot from injury but the aircraft was destroyed beyond repair.

UNDER GERMAN CERTIFICATION
Construction of the third PUL 10 began in 1996 and in 1997 flight testing began at Breitscheid Airfield with German registration. It was reported in the press and it was featured in television and radio news reports. A review of what we learned from the PUL 10 has led to the design of the next generation flying wing, the H 3000.

Technical Data for the PUL 10

H 3000

ADVANCED CONCEPT
From what we have learned from the PUL 9 and the PUL 10 we have developed the H 3000 which has the following improvements:

1. Tandem seating, which allows a lower and narrower cabin. This narrow cabin in a flying wing has less drag than a wide cabin of the same surface area. It gives the pilot, who sits in the front seat, a much better forward view. It also presents better airflow to the propeller.
2. The main gear is in a position that allows the greater convienience of being able to enter the aircraft from the rear rather than from the front.
3. Weight and balance is simplfied by placing the passenger, the fuel and most lagguage precisely on the proper C.G..
4. From computer models we have calculated the design of a radio controlled model with a 5 meter wingspan. We expect to test fly it in the next few months. The construction of the full scale H 3000 prototype is scheduled for 2006. 

 

 

 

Technical data for the H3000
(The performace data of the H 3000 are estimated from data of the PUL 10)

Wing Span 10 m (32.8 ft) Overall Length 4.37 m (14.34 ft) Height 1.40 m (4.59 ft) Wing Area 15.4 m² (165.7 ft²) Empty Weight 290 kg (639 lbs) Gross Weight 500 kg (1102 lbs) Useful Load 210 kg (463 lbs) Fuel Capacity 100 ltr (26.4 gals) Seating 2 Engine Rotax 912 ULS Propeller Variable-Pitch Flaps None Landing Gear Retractable Power (max.) 100PS (99 HP) Cruising Speed 240 km/h (130 kts) Maximum Speed 270 km/h (146 kts) Minimum Speed 58 km/h (31 kts) Range at 75% power 1510 km (815 nm)