IAR-821

IAR-821
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Type:	Agricultural aircraft
Design country:	Romania
Manufacturer:	IRMA (IAR)
First flight:	1967
Commissioning:	1968
Production time:	1968-1969
Number of pieces:	20th

The IAR-821 is an agricultural aircraft produced by the Romanian aircraft construction and repair company Intrepinderea de reparat material aeronautic (IRMA).

development

The IAR-821 was the first in-house development in Romania after the Second World War . The chief designer was Radu Manicatide . The first flight took place in 1967 and production began in 1968.

An Ivchenko AI-14 RF serves as the drive , which drives a constant-speed controllable pitch propeller with three blades.

The IAR-821B version is a two-seater and intended as a training aircraft for spray use. The second driver's seat is located in the place of the original spray agent tank, which has now been replaced by one that has been reduced to 100 liters. The fuel capacity, however, has been increased to 160 liters. This version started for the first time in September 1968.

The pattern, were prepared from the 20 copies until the end of 1969, was prepared by the IAR-822 replaced that a six-cylinder -Motor of Lycoming had as a drive.

construction

The IAR-821 is a single-seat, or, if required, two-seat, low- wing aircraft with a radial engine and a robust, fixed tail wheel landing gear. The fuselage frame consists of welded chrome - molybdenum tubes. The front part is planked with metal, the rear part is covered with fabric. 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 driver's cab is closed and extensively glazed. The cover can be thrown off in an emergency. The tail unit is made of wood and consists of a braced horizontal stabilizer and a two-part elevator , each of which has a trim tab that can be adjusted in flight, as well as a normal vertical tail unit with a bow edge.

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 outer wings made of wood and covered with fabric also house the two fuel tanks with a total capacity of 130 l . The NACA 23012 is used as the wing profile. Like the fuselage, the straight wing center section has a frame made of welded chrome-molybdenum tubes and is clad with a metal paneling that can be walked on. The ailerons are also made of wood and covered with fabric. Simple slotted flaps are used as landing flaps .

Technical specifications

Parameter	Data
crew	1-2
length	9.20 m
span	12.80 m
Wing chord	2.10 m
height	2.78 m
Wing area	26 m²
Wing extension	6.3
Empty mass	1080 kg
Max. Takeoff mass	1900 kg
Top speed	212 km / h
Cruising speed	205 km / h
Application speed	120-150 km / h
Service ceiling	6200 m
Takeoff route	130 m
drive	1 × Ivchenko AI-14 with 300 PS (221 kW)

swell

• Jane's All the World's Aircraft 1971/72