ICA IAR-35
# ICA IAR-35

The ICA IAR-35 is a Romanian glider designed and built in the 1980s primarily for aerobatics, though capable of general purpose use. Several production prototypes were constructed.

## Design and development

The IAR-35 is an all-metal, single seat, short span glider developed for aerobatic flight. Its three spar shoulder wing, with metal ribs and bonded metal skinning, has a constant chord centre section and tapered outer panels. There is no dihedral on the centre section but 2° outboard. The whole trailing edge is occupied by all-metal, statically balanced ailerons, each fitted with an automatic trim tab. DFS (Schempp-Hirth) airbrakes extend both above and below the wings.

Its fuselage is a metal semi-monocoque with aluminium alloy framing and duralumin skin. The cockpit is ahead of the wing with the pilot under a long, single piece Perspex canopy. On the underside, below the wing there is a monowheel, fitted with a brake, which retracts behind a pair of doors. The IAR-35 also has a fixed, semi-recessed tailwheel and a skid under the nose. The wing tips are protected by small, sprung balance wheels. Its fuselage becomes more slender behind the wing, mounting a conventional empennage with tall, straight edged, swept vertical surfaces and a dorsal fillet. The rudder is statically balanced and has a vertical trailing edge. A braced tailplane is mounted forward on the fin, a little above the fuselage, carrying similarly balanced elevators fitted with trim tabs.

The IAR-35 first flew in May 1986. Only a few were built but four remained on the Romanian civil register in 2010.

## Specifications

Data from Jane's All the World's Aircraft 1990/91, Jane's All the World's Aircraft 1988-89

General characteristics

* Crew: One
* Length: 6.47 m (21 ft 3 in)
* Wingspan: 12.0 m (39 ft 4 in)
* Height: 1.72 m (5 ft 8 in)
* Wing area: 10.80 $m^2$ (116.3 sq ft)
* Aspect ratio: 13.3
* Airfoil: NACA 64-015
* Empty weight: 250 kg (551 lb) - 270 kg (595.2 lb)
* Max takeoff weight: 380 kg (838 lb)

Performance

* Stall speed: 86 km/h (53 mph, 46 kn)
* Never exceed speed: 380 km/h (240 mph, 210 kn) in smooth air
* Max rough air speed $(V_A):$ 202 km/h (109 kn; 126 mph)
* g limits: +7 -5
* Maximum glide ratio: 26
* Best glide speed: 100 km/h (54 kn; 62 mph)
* Rate of sink: 0.85 m/s (167 ft/min) *Minimum sink speed: 95 km/h (51 kn; 59 mph)
* Wing loading: 35.19 $kg/m^2$ (7.21 lb/sq ft)
