Aviasud Ultralights Sirocco
ACLA Sirocco NG / Sirocket
Single-seat single-engined high-wing mono-plane with conventional three-axis control. Wing has swept back leading and trailing edges, and constant chord; conventional tail. Pitch control by fully flying tail; yaw control by fin-mounted rudder; roll control by half-span spoilers; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile modified TK7315 McCready; double-surface. Undercarriage has three wheels in tricycle formation with additional tailskid; steel-spring suspen-sion on nosewheel and glass-fibre suspension on main wheels. Push-right go-right nose-wheel steering connected to yaw control. Brake on nosewheel. Glass-fibre/polyester fuselage, partially enclosed. Engine mounted below wing driving pusher propeller. Leading edge in stratified glass-fibre/epoxy and tail in stratified glass-fibre/polyester; fuselage spar bi-directional stratified.
Designed by Frangois Goethals and Ber-nard d'Otreppe who are both engineers, and laid out with the help of a computer, this Sirocco is a result of the experience acquired with the Libellule and although it is of a similar configuration it is a completely new machine, despite the confusion generated by its initial title of Libellule MkIL It is one of the very few microlights which has undergone a complete flight test programme, both static and in flight, Frangois being a specialist in fluid mechanics and Bernard d'Otreppe in the study of composite structures. Out of this programme has come what they believe is the optimum wing profile for the Sirocco, the TK 7315 from the American Paul McCready, with 14% chord thickness.
Amongst the original ideas used on the machine is a foldable wing which can be stored in a tube 19.0ft x 10 inch (5.80 x 0.25 m). The fuselage comes down to 19. 0 x 2.0 x 5.0 ft (5.80 x 0.60 x 1.50 m) which makes for easy transport on a trailer, while alternatively, the wing can be carried on a roof rack and the rest of the machine towed on its own undercarriage. Fitted with an adjustable rudder bar to allow for pilot's height, the Sirocco also has a trimmer for the elevator. Its spoilers seem particularly efficient and it can roll from 45 degree one side to 45 degree the other side in 4 seconds. The Sirocco, the prototype of which made its first flight on the 26 July 1982, has been on sale since January 1983. Options include an instrument panel, VHF or CB radio equipment and a ballistically deployed parachute.
Construction: Aluminium, Fibreglass, Dacron.
Francois Goethals and Bernard D'Otreppes’ company Aviasud built the Sirocco between 1983 and the early 1890.
It was then taken over by Aériane, then the Sirocco license was sold to the ACLA company based in the Netherlands, which produced a modernized version as the Sirocco NG.
The Sirocket comes from a legendary ULM:
There was a major transformation of the prototype Sirocco NG by Dave Stephens and Dean Arnold to create the jet Sirocket classified in the British category of Single Seat Derugalated (SSDR).
Engine: Konig 43RD (430 cc) 27 hp.
Static thrust: 150 lbs.
Empty wt: 252 lbs.
Wing span: 33 ft 2 in.
Wing area: 167 sq.ft.
Length: 19 ft.
Fuel cap; 5 USG.
Max wt: 544 lbs.
Stall: 24 mph.
Max speed: 63 mph.
Vne: 71 mph.
Climb rate: 500 fpm @ 41 mph.
Design limit: +6.7, -3.6g.
Glide ratio: 12-1.
Wing loading: 3.26 lbs/sq.ft.
Power loading: 20.15 lbs/hp.
Engine: JPX PUL425, 26hp at 4600rpm.
Propeller diameter and pitch 39 x 18 inch, 1.00 x 0.45 m.
Max static thrust 150 lb, 68 kg.
Power per unit area 0.17hp/ft., 1.9hp/sq.m.
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre.
Length overall 19.0 ft, 5.80 m.
Height overall 8.9 ft, 2.70 m.
Wing span 33.2 ft, 10. 12 m.
Constant chord 4.6 ft, 1.38 m.
Dihedral 0 degs.
Sweepback 10 degs.
Tailplane span 7.2 ft, 2.20 m.
Fin height 3.7ft, 1.10m.
Total wing area 151 sq.ft, 14.1sq.m.
Total spoiler area 6.9 sq.ft, 0.64 sq.m.
Fin area 4.3 sq.ft, 0.40 sq.m.
Rudder area 4.1 sq.ft, 0.38 sq.m.
Total elevator area 15.6 sq.ft, 1.45 sq.m.
Wing aspect ratio 7.3/1.
Wheel track 5.9 ft, 1.80 m.
Wheelbase 4.7 ft, 1.40 m.
Nose-wheel diameter overall 12 inch, 30 cm.
Main wheels diameter overall 12 inch, 30 cm.
Floats, 10.2ft, 3.10m.
Empty weight 232 lb, 105kg.
Max take-off weight 461 lb, 209 kg.
Payload 229 lb, 104 kg.
Max wing loading 3.05 lb/sq.ft, 14.9 kg/sq.m.
Max power loading 17.7 lb/hp, 8.0kg/hp.
Load factors; +6.7, -3.6 ultimate.
Max level speed 71 mph, 115 kph.
Never exceed speed 75 mph, 120 kph.
Max cruising speed 65 mph, 105 kph.
Economic cruising speed 53 mph, 85 kph.
Stalling speed 24 mph, 40 kph.
Max climb rate at sea level 680 ft/min, 3.5 m/s.
Min sink rate 240 ft/min at 31 mph, 1.2 m/s at 50 kph.
Best glide ratio with power off 12/1 at 40 mph, 65 kph.
Take-off distance 115 ft, 35 m.
Land-ing distance 165 ft, 50 m.
Service ceiling 10,500 ft, 3200 m.
Range at average cruising speed 186 mile, 300 km.
Engine: Rotax 377.
Weight: 128 kgs.
Fuel capacity: 40 Ltr.
Econ cruise speed: 35 kts.
Stall: 22 kts.
Empty weight: 135 kg
Wing span: 10 m
Wing area: 14 sq.m
Fuel capacity: 40 lt
Engine: Rotax 447 ES, 35 hp
MAUW: 240 kg
Max speed: 120 kph
Cruise speed: 100 kph
Minimum speed: 45 kph
Climb rate: 5 m/s
Fuel consumption: 5 lt/hr
Price (1998): 500 000 FB hc