The piston-engined IAR-823 two/five-seat training/liaison aircraft first flew in July 1973 and series production started in 1974. The aircraft has a retractable tricycle undercarriage, two underwing hardpoints for fuel tanks or practice weapons, and is aerobatic under certain payload conditions. Power plant is a 216kW Lycoming IO-540.
Engine: 1 x Lycoming IO-540-G1D5, 215kW / 290 hp Prop: Hartzell Wingspan: 10.0 m / 32 ft 9.25 in Wing area: 15.0 sq.m / 161.46 sq ft Length: 8.24 m / 27 ft 0.25 in Height: 2.5 m / 8 ft 2 in Empty weight aerobatic: 880 kg / 1940 lb Empty weight utility: 900 kg / 1984 lb MTOW aerobatic: 1186 kg / 2614 lb MTOW utility: 1380 kg / 3042 lb Loaded weight: 880 kg / 1940 lb Usable fuel: 90 USG Fuel Burn: 15 USG/Hr Max speed: 300 km/h / 186 mph Max cruise speed 75%: 280 km/h / 174 mph / 151 kt at 5750 ft / 1750 m Service ceiling: 5800 m / 19050 ft ROC: 1378 fpm / 420 m/in Range w/max.fuel: 1350 km / 839 miles 728 nm Range w/max.payload: 700 km / 435 miles / 700 km Seats: 4 Loading: +6/-3 Cabin baggage capacity: 88 lb / 40 kg
Designed for agricul¬tural use the first I.A.R. 822 flew in 1970. Series production started in 1971.
The IAR-822 was the initial single seat version of mixed wood and metal construction. The tandem two seat IAR-822B was used for training and glider towing.
The IAR-826 was as the IAR-822 but of all-metal construction.
IAR-826
IAR-826 Engine: 1 x Lycoming IO-540-G1D5, 215kW Take-off weight: 1900 kg / 4189 lb Loaded weight: 1060 kg / 2337 lb Wingspan: 12.8 m / 41 ft 12 in Length: 9.4 m / 30 ft 10 in Height: 2.8 m / 9 ft 2 in Wing area: 26.0 sq.m / 279.86 sq ft Max. speed: 195 km/h / 121 mph Cruise speed: 170 km/h / 106 mph Ceiling: 4500 m / 14750 ft Range w/max.fuel: 500 km / 311 miles
The IAR-821 is an agricultural crop sprayer and duster aircraft. The design was completed under the leadership of eng. Radu Manicatide in 1967, at IMFCA Bucharest (Institutul de Mecanica Fluidelor si Cercetari Aerospatiale – Institute of Fluid Mechanics and Aerospace Research).
A low-wing monoplane, it featured mixed wood-metal structure, with the fuselage and wing roots built from welded chrome-molybdenum tube, and the outer wings and tail unit from wood. The three-part, self-supporting rectangular wing is attached to the fuselage with a 5 ° angle of incidence. While the wing center part is designed without a V-position up to about 1/3 of the span, the wing ends have a V-position of + 5 °. The wing center section, which runs straight through, has a frame of welded chrome-molybdenum tubes and is clad with metal planking that can be walked on. The outer wings made of wood and covered with fabric also house the two fuel tanks with a total capacity of 130 lt. The front fuselage had aluminium panels, while the rest of the surface was plywood covered with fabric.
The ailerons are also made of wood and covered with fabric. As landing flaps simple slotted flaps are used. The container for 800 kg of spray is located between the fire bulkhead and the cockpit. Both solid and liquid funds can be applied.
The propulsion was provided by an Ivchenko AI-14 RF, a single row air-cooled 9-cylinder radial capable of delivering 300 hp (221 kW), located at the apex of the front fuselage contained in a NACA cowling and combined with a three-blade propeller with fixed pitch. It was with fixed, tailwheel undercarriage.
It was built at IRMA (Intreprinderea de Reparatii Material Aeronautic – Enterprise for Aeronautical Material Repairement), in Bucharest, first flying in 1967. A small series of 20 aircraft was produced in 1968 and 1969, plus a single example of a trainer aircraft designated IAR-821B that had a second cockpit installed in place of the IAR-821’s chemical tank, and was equipped with a new chemical tank of smaller capacity (100 lt). The fuel capacity was been increased to 160 lt. This version flew for the first time in September 1968. It was intended that this aircraft should equip Romanian flying schools from 1969, but this did not happen.
IAR-821B
The IAR-821 was built until the end of 1969, when replaced by the IAR-822 which had a six-cylinder Lycoming engine.
IAR-821 Engine: 1 × Ivchenko AI-14RF, 220 kW (300 hp) Wingspan: 12.80 m (42 ft 0 in) Wing area: 26.0 sq.m (280 sq ft) Wing profile: NACA 23012 Wing chord: 2.10 m Wing extension: 6.3 m Length: 9.20 m (30 ft 2 in) Height: 2.78 m (9 ft 1.5 in) Empty weight: 1,080 kg (2,380 lb) Gross weight: 1,900 kg (4,180 lb) Capacity: 600 kg (1,300 lb) chemicals Maximum speed: 212 km/h (132 mph, 115 kn) Cruising speed: 205 km / h Application speed: 120-150 km / h Endurance: 2 hours 36 minutes Service ceiling: 6,200 m (20,300 ft) Rate of climb: 8.0 m/s (1,575 ft/min) Takeoff roll: 130 m Crew: One pilot
A 1960 product of the Rumanian aircraft industry was the general purpose IAR 818 derived from the earlier IAR 817. The I.A.R. 818 first flew in 1960 and was reported to possess a maximum speed of 115 mph (185 kph) and normal and maximum ranges of 298 mls (480 km) and 603 mls (970 km) respectively, the IAR 818 is suitable for agricultural and ambulance duties.
IAR.818 Engine: 1 x M-337, 155kW Take-off weight: 1300 kg / 2866 lb Loaded weight: 825 kg / 1819 lb Wingspan: 12.1 m / 39 ft 8 in Length: 10.0 m / 32 ft 10 in Wing area: 25.4 sq.m / 273.40 sq ft Max. speed: 185 km/h / 115 mph Cruise speed: 165 km/h / 103 mph Ceiling: 4000 m / 13100 ft Range w/max.fuel: 900 km / 559 miles Range w/max.payload: 250 km / 155 miles
In 1955, a prototype of a new utility aircraft, the IAR-817, was first flown at the URMV-3 works of Industria Aeronautică Română at Brașov. The URMV-3 works had been formed at the Sovromtractor tractor factory, itself on the site of the Industria Aeronautică Română aircraft works. It was a single-engine high-wing monoplane with a pod-and-boom type fuselage of welded steel tube construction and fabric-covered wooden wings. It had a fixed tricycle undercarriage. The aircraft was powered by a single 120 kW (160 hp) Walter Minor 6-III air-cooled six-cylinder inverted inline engine.
An air-ambulance version of the IAR-817, the IAR-817S, entered production in 1957, with over 60 built.
The type formed the basis of the IAR-818, built from 1961.
Engine: 1 × Walter Minor 6-III, 120 kW (160 hp) Propeller: 2-bladed variable-pitch Wingspan: 12.6 m (41 ft 4 in) Wing area: 25.4 m2 (273 sq ft) Length: 9.8 m (32 ft 2 in) Height: 3.4 m (11 ft 2 in) Empty weight: 800 kg (1,764 lb) Max takeoff weight: 1,150 kg (2,535 lb) Maximum speed: 175 km/h (109 mph, 94 kn) Cruise speed: 165 km/h (103 mph, 89 kn) Stall speed: 70 km/h (43 mph, 38 kn) Range: 560 km (350 mi, 300 nmi) Ferry range: 930 km (580 mi, 500 nmi) Service ceiling: 3,000 m (9,800 ft) Time to 1,000 m (3,300 ft): 7 minutes 30 seconds Take-off run: 150–180 m (490–590 ft) Landing run: 60 m (200 ft) Crew: 1 or 2 Seats: 4-5
The IAR 813 is a two-seater light sports and training aircraft developed from the earlier IAR 811. The IAR 813 is a low-wing cantilever monoplane of wooden and composite construction powered by a Walter Minor 6-III six-cylinder in-line inverted air-cooled engine providing a top speed of 185km/h and a range of 500km.
Engine: 1 x Walter Minor 4-III, 77kW Take-off weight: 760 kg / 1676 lb Empty weight: 520 kg / 1146 lb Wingspan: 10.1 m / 33 ft 2 in Length: 8.4 m / 27 ft 7 in Height: 2.3 m / 7 ft 7 in Max. speed: 190 km/h / 118 mph Cruise speed: 175 km/h / 109 mph Ceiling: 5500 m / 18050 ft
Making its first flight in December 1985, the IAR-99 Soim (Falcon) is designed as a basic jet trainer/light ground attack aircraft, the Soim has lateral intakes for the single 4,000 lb st (17,8 kN) R-R Viper Mk 632-41 turbojet. The wings are unswept, with provision for up to four attachment points, as well as a gun pod on the fuselage centreline. Maximum take-off weight is in the 5,500kg class, with a maximum level speed of 865km/hr (467kt) and a service ceiling of 13,900m (46,000ft).
The first prototype flew on December 21, 1985. The aircraft was in production for the Romanian Air Force to replace the L-29 Delfin in Romanian Air Force service.
IAR 99 Soim Engine: 1 x Rolls-Royce “Viper” Mk.632-41M, 1820kg Take-Off Weight: 4400-5560 kg / 9700 – 12258 lb Empty Weight: 3200 kg / 7055 lb Wingspan: 9.85 m / 32 ft 4 in Length: 11.01 m / 36 ft 1 in Height: 3.90 m / 12 ft 10 in Wing Area: 18.71 sq.m / 201.39 sq ft Max. Speed: 865 km/h / 538 mph Ceiling: 12900 m / 42300 ft Initial ROC: 2190 m / min. T/O run: 790 m. Ldg run: 750 m. Hardpoints: 4. Range: 970-1100 km / 603 – 684 miles Crew: 2 Armament: 1 x 23mm cannon, up to 800kg of weapons
The prototype IAR 471 dive bomber passed the design status and was completed. However, before its maiden flight, this prototype was destroyed in the US raid against the IAR Brasov plants, on May 6, 1944.
Expansion of the operational versatility of the basic IAR.80 design to embrace the fighter-bomber and dive bomber tasks resulted in the I.A.R.81, which was to fly its first operational sorties in the Ukraine on 15 October 1941. The 25th production I. A.R.80A was taken from the line to serve as a prototype, fitted with two wing racks for 50kg bombs and a ventral crutch for a 225kg bomb. Introduction of the crutch dictated modifications to the main undercarriage members and an automatic flap actuating device was introduced. The dual fighter-bomber and dive bomber version became known as the BoPi, an acronym for Bombardier in Picaj, or dive bomber. The I.A.R.81 retained the six 7.92mm FN-Browning guns and could carry three 100kg bombs, or one 225kg and two 50kg bombs. Fifty I.A.R.81s were followed by a batch of 10 I.A.R.81As, which, like the final 10 I.A.R.81s, were armed with two 13.2mm and four 7.92mm guns, and these proved to be the last of the BoPi aircraft. The next production version, the I.A.R.81C, was a pure fighter and was to be built in larger numbers than any I.A.R. 80 variant. Essentially similar to the I.A.R.80C apart from having the Ikaria cannon replaced by the Mauser MG 151 and retaining only two 7.92mm guns, the I.A.R.81C was, like other versions of the I.A.R.81, powered by the I.A.R.-K 14-1000A engine. A total of 161 I.A.R.81Cs was built by late 1943 when licence manufacture of the Bf 109G-6 took over. The maiden flight of the first IAR 81C, No 301, was performed on April 6, 1943. Until June 1, 26 sub versions of the IAR.80/81 had already been finished and test flown.
IAR-81 fighter-bomber equiv. to IAR-80A Wingspan: 10m Armament: 6 x FN-Browning 7.92mm mg initial production: belly-rack (1 x 225kg bomb), 40 built late production: belly-rack + 2 x wing rack (50kg bomb), 10 built
IAR-81A BoPi equiv. to IAR-80B Wingspan: 10m Armament: 4 x 7.92mm mg + 2 x 13.2mm mg 10 built Orig. 20 IAR-81s ordered deliv. w/o bomb racks as IAR-80B fighters
IAR-81B Project Range: 695 km Ikaria cannon-armed vers., deliv. as IAR-80C fighters
IAR-81C as ’81B Wingspan: 11m Range: 730 km Armament: 4 x 7.92mm mg + 2 x 20mm MG151 150 built (up to 165)
IAR-81M 1944-45 conv. program to uprate earlier IAR-81 models to IAR-81C Wingspan: 11m Armament: 4 x 7.92mm mg + 2 x MG151/20
Take-off weight: 3070 kg / 6768 lb Empty weight: 2125 kg / 4685 lb Wingspan: 10.52 m / 34 ft 6 in Length: 8.97 m / 29 ft 5 in Height: 3.60 m / 11 ft 10 in Wing area: 16.00 sq.m / 172.22 sq ft Max. speed: 542 km/h / 337 mph Range: 1030 km / 640 miles
Provisional design work on a monoplane fighter with retractable landing gears was privately started by a small JAR team in early 1936, to be abandoned at the end of the year due to lack of interest shown by authorities. Corrupt members of the Romanian government had already influenced the military to place a substantial order for the ill fated PZL P.11. However, the design was secretly warmed up in mid 1937 and eventually lead the prototype of an aircraft comparable to the main fighter designs of those pre war years. Designed as a successor to the licence-built P.Z.L. P.24E by a team comprising Ion Grosu, Ion Cosereanu, Gheorghe Zotta and Gheorghe Vallner, the I.A.R.80 single-seat fighter was flown on 20 April 1939 in the hands of Capitan Aviator Constantin Pufi Popeseu, IAR’s chief test pilot. The prototype was powered by a 900hp I.A.R.-K 14-II C32 14- cylinder air-cooled radial based on the Gnome-Rhone 14K Mistral-Major and its armament consisted of two wing-mounted 7.92mm FN-Browning guns. The series-production I.A.R.80 appeared in the spring of 1940, and featured a 52cm increase in wing span, a 74cm increase in fuselage length, greater fuel capacity, an aft-sliding cockpit canopy, an armament of four 7.92mm guns and a 930hp I.A.R.-K 14-III C36 engine. The series model also discarded the tailplane bracing struts featured by the prototype. The first flight of an initial series production dive bomber, the IAR 81, No 81, happened on August 16,1941. The I.A.R.80 achieved operational capability on 14 January 1941 with Flotilla 2 Vinatoare of the Royal Air Forces of Romania (Fortelor Aeriene Regal ale Romania), or FARR. The 50th and last of the initial series (No 175) left the production line in April 1942, and was fitted with an extra pair of guns, this six-gun armament being standardised for subsequent aircraft, which were designated I.A.R.80As, these also having racks for two 50kg bombs and being powered by the 1,025hp I.A.R.-K 14-1000A engine. Ninety I.A.R.80As were followed by 50 I.A.R.80Bs, with an armament of four 7.92mm and two 13.2mm guns, the 21st and subsequent aircraft of this batch having a further increase in wing span of 48cm and provision for underwing drop tanks. Manufacture of the pure fighter version of the basic design was completed with 50 I.A.R.80Cs – originally laid down as I.A.R.81Bs, which see – with 20mm Ikaria cannon replacing the 13.2mm weapons and reintroducing the tailplane bracing struts. A small number of I.A.R.80s remained in Romanian service until late 1949, after which survivors with the lowest hours were rebuilt as I.A.R.80DC tandem-seat dual-control advanced trainers. The Junkers Jumo 211Da was not the only in line engine to be experimentally fitted to an IAR 80 airframe. At the end of June 1943, several test flights were performed with an IAR 80 fitted with a Daimler Benz DB 601Aa from a Messerschmitt Bf 109E.
IAR-80 prototype 1939 Engine: 870hp IAR K14-III C32 Wingspan: 10m open cockpit Armament: 2 [or 4?] x FN-Browning 7.92mm
IAR-80 initial production 1941 Engine: 930hp K14-III C36 Wingspan: 10.52m Armament: 4 x 7.92mm 20 built
IAR-80 (No.13) April 1941 Engine: 1100hp DB 601Aa (from Bf-109E) Wingspan: 10.52m
IAR-80 late production 1941 Engine: 960 hp IAR K14-IV C32 Armament: 4 x 7.92mm 30 built
IAR-80A Engine: 1025hp IAR K14-1000A Armament: 6 x FN-Browning 7.92mm reinforced rear fuselage, additional armour protection
IAR-80B Wingspan: 11.00 m / 36 ft 1 in Length: 8.97 m/ 29 ft 5 in Height: 3.52 m / 11 ft 7 in Wing area: 16.50 sq.m / 177.60 sq ft Take-off weight: 2980 kg / 6570 lb Loaded weight: 2200 kg / 4850 lb Max. speed: 550 km/h / 342 mph Range: 730km, drop tank 1030km Armament: 4 x FN-Browning 7.92mm mg + 2 x FN-Browning 13.2mm mg 50 built
IAR-80B (No.326) June 1943 Engine: 1475hp DB-605A for trials
I.A.R.80C Wingspan: 11.00 m / 36 ft 1 in Length: 8.97 m/ 29 ft 5 in Height: 3.52 m / 11 ft 7 in Wing area: 16.50 sq.m / 177.60 sq ft Take-off weight: 2980 kg / 6570 lb Loaded weight: 2200 kg / 4850 lb Max. speed: 550 km/h / 342 mph Armament: 4 x FN-Browning 7.92mm + 2 x 20mm Ikarus 50 built
IAR-80DC Postwar conv. to 2-seat trainer (fuselage fuel tank removed)
IAR-80M 1944-45 conv. to uprate IAR-80 gun armament to IAR-81C standards
IAR-80 one conv. Engine: 1600hp engine [Gnome-Rhône 14R?]
