Lombarda Bonomi BS-02 Balestruccio

The Balestruccio was a single seat glider with a high aspect ratio gull wing built in four parts. The two inner panels, straight edged with constant chord and carrying dihedral, joined on top of the fuselage, their extremities braced from the lower fuselage with flat steel V-struts, encased in faired wood to reduce drag and assisted on each side by a pair of jury struts. The upper end of each strut was attached on one of the two wing spars. The outer wing panels were straight tapered, with rounded tips. There were differential ailerons on the outer trailing edges and flaps inboard.

The fuselage of the Balestruccio was hexagonal, with deep, near vertical sides. Its comfortable cockpit was immediately in front of the wing leading edge and was originally provided with a wooden canopy with small side openings, similar to that used on the German DFS Fafnir, but this was later replaced with a more conventional open arrangement which provided better all-round visibility. A single, sprung skid and a tail bumper provided an undercarriage. The fuselage tapered aft to a mid-mounted horizontal tail consisting almost entirely of the elevator; although this had straight leading edges, a combination of their slight sweep and the full, rounded trailing edges gave the planform an almost elliptical appearance. There were aerodynamic balances and a large cut-out for rudder movement. As first constructed, the vertical tail was rather similar, with a small fin and a full, deep, curved, balanced rudder which extended slightly below the keel. Later, with the fuselage shortened by one frame or about 700 mm (28 in), the Balestruccio was given a new, angular fin and rudder with straight taper and square tip. Like the old rudder, this was also balanced and deep, though extending only to the keel. The original horizontal tail was retained.

The Balesruccio proved to be versatile and efficient and was flown by Vittorio Bonomi and Enrico Rolandi from Mottarone and Campo dei Fiori di Varese. On 18 December 1932 Rolandi flew it for 25.8 minutes, setting a new Italian national endurance record, covering 15.7 km (9.8 mi) and winning the Castiglione Trophy. As late as 1937, it was demonstrating its performance in Asiago.

Wingspan: 18.00 m (59 ft 1 in)
Wing area: 17.14 m2 (184.5 sq ft)
Aspect ratio: 18
Wing section: Gottingen 549
Length: 8.33 m (27 ft 4 in), later 7.55 m (24 ft 9 in)
Empty weight: 125 kg (276 lb)
Gross weight: 205 kg (452 lb)
Wing loading:11.50 kg/m2 (2.36 lb/sq ft)
Maximum glide ratio: estimated 24:1
Rate of sink: 0.58 m/s (114 ft/min)
Crew: One

LOM Praha M-332 / Avia M 332 / Walter M 332

LOM Praha M-332 AK

The Avia M 332 (originally known as the Walter M332) is an air-cooled four-cylinder inverted inline engine. It was designed by Bohumil Šimůnek, of Motorlet Walter Aircraft Engines, as a more powerful replacement for the four-cylinder Walter Minor engine, going into production in 1958. Piston aircraft engine production was transferred from Walter to Avia in 1964, the engine becoming the Avia M 332.

Applications
Aero 145
Carlson Criquet
Fry Esprit VFII
Orličan L-40 Meta Sokol
Rolandas Kalinauskas RK-5 Ruth

Specifications
Type: 4-cylinder inverted air-cooled supercharged inline engine
Bore: 105 mm (4.13 in)
Stroke: 115 mm (4.53 in)
Displacement: 3.98 L (247.9 in³)
Length: 1,102 mm (43.4 in)
Width: 425 mm (16.7 in)
Height: 628 mm (24.7in)
Dry weight: 102 kg (225 lb)
Valvetrain: two camshaft operated valves per cylinder, sodium filled exhaust valve
Supercharger: Centrifugal
Fuel system: Low pressure fuel injection
Fuel type: Min 72 octane unleaded or 80 octane leaded
Oil system: Dry sump pressure feed
Cooling system: Air-cooling
Power output: 104 kW (140 hp) at 2,700 rpm (take-off)

Lolo Pipistrel Spider

A trike of welded steel construction, power units options are the Rotax 503 or 912, and wings are 10, 1, or 15 sq.m.

Empty weight: 165 kg
Wing span: 11 m
Wing area: 13 sq.m
Fuel capacity: 42 lt
Certification: A
Engine: Rotax 582, 65 hp
MAUW: 400 kg
Seats: 2
Max speed: 100 kph
Cruise speed: 70 kph
Minimum speed: 42 kph
Climb rate: 8 m/s
Fuel consumption: 8 lt/hr
Price (1998): 250 000 AS

Loire-Nieuport LN.40 / LN.401 / LN.411

The LN.40 was evolved from the Nieuport 140 in response to a French naval requirement for a ship-borne dive-bomber, and emerged as a compact single-seater with inverted gull wings and a crutch to lever the single large bomb clear of the propeller before release. The prototype flew in June 1938, trials revealing the need for tail modifications. It was also decided to use the extended main landing gear legs as dive brakes, allowing the removal of the tail-mounted dive brakes. Some 42 LN.401 production aircraft were ordered, although only 23 or so had been delivered by the fall of France. The French Air Force also ordered 40 LN.411s, these having no arrester hook, wing-folding mechanism or flotation bags; again only about 23 had been delivered by the fall of France. After the Armistice SNCASO assembled another 24 LN.401s and LN.411s from components.

LN.401
Span: 14m (45ft 11.25 in).
Length: 9.75m (3l ft 11.75in).
Powerplant: l x Hispano-Suiza l2Xcrs, 515kW (690 hp)
Max TO weight: 2825 kg (6,228 lb).
Max speed: 236 mph at 13,125 ft.
Operational range: 746 miles.
Armament: 1 x 20-mm Hispano¬-Suiza cannon and two 7.5-mm (0.295-in) Darne mg plus provision for 1 x 225-kg (496-lb) bomb carried under the fuselage.

LN.411