1 engine

Rogožarski AŽR

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The Rogožarski AŽR (Serbian Cyrillic: Рогожарски АЖР) was a single-engined, two-seat biplane aircraft designed as a trainer in Yugoslavia before World War II. It was designed by Viljem Šuster and built at the Rogožarski factory in Belgrade.

The aircraft was a biplane with the lower wing smaller than the upper. It was equipped with a seven-cylinder Walter Castor air-cooled radial engine of 240 hp and a wooden double-bladed propeller. The plane had dual controls, the two crew (pilot and flight instructor), sat one behind the other. It was to be employed as an intermediate trainer, replacing the outdated Hansa-Brandenburg C.I. The fuselage, which was of rectangular cross-section, was made of wood and covered with plywood. The wings had rounded ends, each was connected by a pair of metal struts and wire tensioners. Construction of the wing involved the use of wood covered with canvas. The landing gear was fixed and had no axle.

The first flight was conducted by a factory test pilot on November 5, 1930 and after the completion of factory tests, was handed over to the Yugoslav Royal Air Force Commission for testing.

The AZR was planned to replace the obsolete Hansa Brandenburg aircraft in the future. However, the flight characteristics were lower than the requirements, and they refused mass production.

The aircraft was only used in 1931 for advertising purposes, demonstration flights and participation in air shows. It also competed in the King’s Cup and the like; AZR still hoped to come to some arrangement with the military. This did not happen, Rogozarski withdrew from aircraft design, the prototype was registered as a civilian plane and used by the factory. It received the civil registration UN-PAU. In the meantime, the economic situation was such that the AŽR was standing in its hangar, waiting for better days; despite bank loans, there was a distinct lack of orders and the company went bankrupt in 1933.

Circumstances improved in the summer of 1934 when the Yugoslav Air Force bought the AZR and the fortunes of the factory improved, becoming a shareholder company. The AŽR was used as a trainer until 1937.

Engine: 1 × Walter Castor 7-cyl radial, 176 kW (236 hp)
Propellers: 2-bladed
Wingspan: 10.55 m (34 ft 7 in)
Wing area: 27.00 sq.m (290.6 sq ft)
Length: 7.55 m (24 ft 9 in)
Height: 3.05 m (10 ft 0 in)
Empty weight: 859 kg (1,894 lb)
Gross weight: 1,433 kg (3,159 lb)
Maximum speed: 215 km / h
Cruising speed: 185 km / h
Range: 745 km (463 mi; 402 nmi)
Service ceiling: 5,320 m (17,450 ft)
Rate of climb: 4.78 m/s (941 ft/min)
Crew: 2

Rogožarski SIM-II

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Engine: Siemens Sh 14, 82 kW (110 hp)
Propeller: 2-blade
Wingspan: 12.40 m (40 ft 8 in)
Wing area: 21.70 sqm (233.6 sq ft)
Length: 7.80 m (25 ft 7 in)
Height: 2.68 m (8 ft 10 in)
Empty weight: 520 kg (1,146 lb)
Gross weight: 770 kg (1,698 lb)
Maximum speed: 105 km/h (65 mph; 57 kn) 148 km/h at sea level
Range: 750 km (466 mi; 405 nmi)
Service ceiling: 5,000 m (16,404 ft)
Crew: 2

Rogožarski Brucoš

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The Rogožarski Brucoš (Freshman, Serbian Cyrillic: Рогожарски Бруцош) was a single-engine, two-seat, low wing monoplane aircraft designed as a trainer in Yugoslavia in 1940. It was designed and built in the Rogožarski aircraft factory in Belgrade. Only one prototype was built.

Engine: 1 × de Havilland Gipsy Major I, 96 kW (129 hp)
Propeller: 2-bladed
Wingspan: 10.00 m (32 ft 10 in)
Wing area: 16.00 sq.m (172.2 sq ft)
Length: 8.10 m (26 ft 7 in)
Height: 3.10 m (10 ft 2 in)
Empty weight: 615 kg (1,356 lb)
Gross weight: 872 kg (1,922 lb)
Maximum speed: 185 km/h (115 mph; 100 kn) 210 km/h at sea level
Range: 840 km (522 mi; 454 nmi)
Service ceiling: 4,000 m (13,123 ft)
Rate of climb: 2.54 m/s (500 ft/min)
Crew: 2

Rogožarski SIM-XII / Рогожарски СИМ-XII-Х

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Rogožarski SIM-XII-H (left) and SIM-XIV-H (right) (Kumbor 1938)

The Yugoslav Royal Air Force turned to the Rogožarski factory for seaplane pilot trainers in 1937. A requirement was the seaplane would match the characteristics of the SIM-X. Since it was not possible to adapt existing SIM-X for installation of EDO floats, chief designed Sima Milutinović fitted the new, larger plane with a more powerful Walter Major 6 190 hp engine. At the end of 1937 the prototype was ready for testing. The first flight was conducted on February 7, 1938, by test pilot Ivan Koroša in at Divulje. After the flight tests had achieved satisfactory results, the first batch of aircraft was ordered, which were delivered in mid-1939.

The SIM-XII-H two-seat plane, with engine Walter Major 6 (190 hp), was of predominantly wooden construction, with an elliptical cross-section of fuselage entirely made of wood and covered with plywood. The wings were wood covered with fabric, with rounded ends. On each side, the wings are supported by a pair of inclined struts attached to the fuselage. The fuel tank was located in the central section between the wings. The first series of aircraft had two EDO Model 47 floats installed.

Nine were built in total.

The Royal Maritime Navy signed a contract with the Rogožarski factory on July 15, 1940 for a second series of these plane (4 aircraft) with these seaplanes equipped for instrument, or, “blind” flying. Rogožarski delivered these aircraft in five months but without floats as the delivery from Canada was delayed for several months. With agreement reached between the Rogozarski factory an the Navy command, the design and development of domestic aircraft floats was launched, unfortunately this project did not reach completion due to the outbreak of April war . In the pre-war period two SIM-XII-H aircraft were in accidents both in Boka Kotorska in 1940. Both aircraft were designated for disposal, so the Navy Command requested approval to install the floats from these planes onto new aircraft (onto the 2nd series of SIM-XII-H) considering that these planes were equipped with instruments for instrumental (“blind”) flying. When the approval was given, the floats were installed into new planes, so the aircraft in the second series in use before the war broke out.

The type was retired in 1941.

Rogožarski SIM-XII-H
Engine: 1 × Walter Major 6, 6-cylinder line, 140 kW (190 hp)
Propellers: 2-bladed
Length: 7.50 m (24 ft 7 in)
Wingspan: 11.00 m (36 ft 1 in)
Height: 2.96 m (9 ft 9 in)
Wing area: 2,050 m2 (22,100 sq ft)
Empty weight: 635 kg (1,400 lb)
Gross weight: 920 kg (2,028 lb)
Maximum speed: 208 km/h (129 mph; 112 kn) at sea level
Range: 840 km (522 mi; 454 nmi)
Crew: 2

Rogožarski SIM XI

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The Rogožarski management observed that the SIM-X characteristics were very close to an acrobatic plane. It was decided to make some modifications to make an acrobatic plane. Sima Milutinovic designed reinforcements, reducing the wing area, and more powerful engines during 1937.

The Rogozarski SIM-XI (Serbian: Рогожарски СИМ-XI) was a single engined, one crew, high wing monoplane, designed and built at the Rogožarski factory in Belgrade.

The test flying was conducted by factory test pilot Captain Milan Bjelanovic by the end of January 1938. Factory tests were carried out until 12 March, then tests the experiment group of the Yugoslav Royal Air Force. The plane got excellent grades and and the YAF bought the prototype SIM-XI. This was the first Yugoslav aerobatic aircraft.

Engine: 1 × Siemens Sh14a, 110 kW (150 hp)
Propeller: 2-blade
Wingspan: 9.40 m (30 ft 10 in)
Wing area: 17.30 sq.m (186.2 sq ft)
Length: 7.16 m (23 ft 6 in)
Height: 2.70 m (8 ft 10 in)
Empty weight: 540 kg (1,190 lb)
Gross weight: 680 kg (1,499 lb)
Maximum speed: 191 km/h (119 mph; 103 kn)
Cruising speed: 168 km/h (104 mph; 91 kn)
Minimum control speed: 88 km/h (55 mph; 48 kn)
Range: 825 km (513 mi; 445 nmi)
Service ceiling: 5,500 m (18,045 ft)
Rate of climb: 4.87 m/s (959 ft/min)
Crew: 1

Rogožarski SIM-X / SEA-JEEP / SI-GIP

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Aircraft SIM X was designed by Sima Milutinovic at the beginning of the 1936, drawing on the positive experiences of his previous SIM-II and SIM-VIII. The Rogozarski SIM-X (Serbian: Рогожарски СИМ-X) was a 1936s Yugoslav Sports and tourist plane and for basic training of military pilots. It was designed and built at the Rogožarski factory in Belgrade.

The prototype aircraft was built at Rogožarski from August until the end of the 1936. The first test flight took place on 1936. The SIM X had parasol monoplane with one engine, a wooden two blade propeller, with two crew members in tandem. The aircraft was registered YU-PDY.

While the plane was designed for three types of engine mounting: Walter NZR 120 hp, Siemens 110 hp and Gypsy Major 120 hp: the production incorporated a Walter NZR 120 hp air-cooled radial with reduction gear which was produced locally by Vlajković in Belgrade. The plane was mostly wooden construction, the fuselage of elliptical cross-section made entirely of wood covered with plywood, and the wings made of wood covered with cloth, with rounded ends. On each side, the wings are supported by a pair of inclined struts from the fuselage. The fuel tank was located in the central part between the wings. Landing gear was fixed, no axles, completely made of steel pipe.

A trainer single-engine two-seater plane for the initial training (21 units, 1937)

The Rogožarski SEA-JEEP was a modification of SIM X with Gypsy Major engine (1 converted SIM-X, 1940)
A second Rogožarski SEA-JEEP was a modified SIM-X plane for a school night flying (1 converted SIM-X 1941)

Variants:
Rogozarski SIM-X First variant with Walter NZR engines 120 hp, 21 built (1) prototype 1936 (10 airplane) 1937 and (10 airplane) 1938

Rogozarski SI-GIP
Second variant with Gipsy Major engines 132 hp, 1 built (conversion) in 1940.

Rogozarski SIM-Xa
Third variant instrument flight aircraft with Walter NZR engines 120 hp, 1 built (conversion) in 1941.

Engine: 1 × Walter NZR 6-cylinder radial, 89 kW (120 hp)
Propellers: 2-bladed Crew: 2
Wingspan: 10.00 m (32 ft 10 in)
Wing area: 18.50 sq.m (199.1 sq ft)
Length: 6.96 m (22 ft 10 in)
Height: 2.70 m (8 ft 10 in)
Empty weight: 543 kg (1,197 lb)
Gross weight: 785 kg (1,731 lb)
Maximum speed: 202 km/h (126 mph; 109 kn)
Cruising speed: 168 km/h (104 mph; 91 kn)
Minimum control speed: 72 km/h (45 mph; 39 kn)
Range: 560 km (348 mi; 302 nmi)
Service ceiling: 5,500 m (18,045 ft)
Rate of climb: 4.17 m/s (821 ft/min)

Rogožarski SIM-VI

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SIM VI

The Rogožarski SIM-VI (Serbian Cyrillic:Рогожарски СИМ-VI) was designed by engineer Sima Milutinović in the early 1930s as an inexpensive trainer plane that would enable expansion of sports aviation. It was a single-engined, two-seat, low wing aircraft designed as trainer in Yugoslav before World War II. It was designed and built at the Rogožarski factory in Belgrade.

The project was in suspension until 1936, when a prototype was constructed, and the maiden flight was made in 1937. The aircraft was a low wing monoplane of fabric-covered wooden structure. A four cylinder 50 hp / 35 kW Walter Mikron engine drove a two-bladed wooden propeller. The plane had tandem seating and was intended for civilian use, for the training of sports pilots, demonstration flights and travel. The wings were of thin profile, only 6% of trapezoidal shape with rounded ends. On each side, the wings were stretched with molded wire ties.

Immediately after completing the flight tests of aircraft SIM-VI, engineer Milutinovic undertook the repair of the shortcomings he had observed, so that by the end of the 1937 Rogozarski had a new variant of this airplane which was designated SIM-VI-a. It had a more powerful engine Walter Mikron II 44 kW (60 hp). An increase in engine power required strengthening of the basic structure which Milutinovic used to make general improvements to the aircraft. Wing relative thickness was increased from 6% to 15% which strengthened the wings, and resulting in the removal of wire ties. Now the wings were covered with cardboard to the half swing instead of cloth which resulted in an improved overall stiffness of the aircraft. This also enabled the landing gear and aerodynamic characteristics of new aircraft to be upgraded, while the weight was only slightly increased.

After successful testing and registration (YU-PDX) the SIM-VI was bought by the Central Administration of the Aero Club, which used the it at airshows and for the training of sport pilots. The aircraft did not enter serial production because it could not be used at smaller and under-equipped airports that existed in central Serbia.

Flight tests that were carried out at the Zemun airfield proved that the SIM-VI-a had slightly better performance than its predecessor, and was able to perform basic stunts. After being granted a navigation license the plane was registered under civil designation YU-PEZ and it was bought by Aero Club’s Central Administration. The plane was used until the beginning of the war in 1941 at air shows, sports competitions and for pilot training.

Pilot and engineer Arsenijevic, piloted this plane at the competition Little Entente states in 1938. during the competition the plane flew some 3,274 km (2,034.37 miles) achieving an average speed of 151.01 km/h (93.83 mph). Pilots who flew the plane felt that the plane was agile and easy to operate and fly, but despite good features and relatively low cost, SIM-VI did not go into serial production it could not win over the traditional empirical approach (a robust and powerful aircraft is a good aircraft). Right before the outbreak of war, the aircraft was included into the Yugoslav Royal Air Force, deployed as a signalling plane but was destroyed during the bombing of Lazarevac airfield on 7 April 1941.

Engine: 1 × Walter Mikron, 37 kW (50 hp)
Propeller: 2-bladed
Wingspan: 9.50 m (31 ft 2 in)
Wing area: 15.00 m2 (161.5 sq ft)
Length: 7.05 m (23 ft 2 in)
Gross weight: 500 kg (1,102 lb)
Empty weight: 300 kg (661 lb)
Maximum speed: 120 km/h (75 mph; 65 kn) 150 km/h (93 mph) at sea level
Cruising speed: 60 km/h (37 mph; 32 kn)
Range: 450 km (280 mi; 243 nmi)
Service ceiling: 4,000 m (13,123 ft)
Crew: 2

Rogožarski Fizir FN / Zmaj Fizir FN

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The Fizir FN (Физир ФН in Serbian) was a plane designed by Croatian Rudi Fizir for primary training in Yugoslavia before World War II.

Fizir FN was single-engine two-seat, trainer biplane with one pair of struts on each side. The wings are rounded at the ends of the flaps had been located on the lower and upper wings.

The first prototype Fizir FN (Fizir teaching) was designed and manufactured in 1929.

Fizir in Petrovaradin did not have the capacity for industrial production of aircraft, their area of work was the design and prototyping. It was built at the Zmaj Zemun and Rogožarski factory in Belgrade, and Albatros in Sremska Mitrovica.

Forty examples were built.

Variants:

Fizir FN – Mercedes – Mercedes 88 kW

Fizir FN – Walter – Walter NZ-120 88 kW

Fizir FN – Walter-Mars 106 kW
Seaplane nicknamed “Little Fizir” or “Fizir Mars”.

Zmaj Fizir FN
Engine: 1 × Walter NZ-120, 88 kW (118 hp)
Propeller: 2-blade
Wingspan: 11.20 m (36 ft 9 in)
Wing area: 32.50 sq.m (349.8 sq ft)
Length: 8.80 m (28 ft 10 in)
Height: 3.10 m (10 ft 2 in)
Empty weight: 820 kg (1,808 lb)
Gross weight: 1,426 kg (3,144 lb)
Maximum speed: 120 km/h (75 mph; 65 kn) 140 at sea level
Range: 540 km (336 mi; 292 nmi)
Service ceiling: 6,500 m (21,325 ft)
Crew: 2

Rogožarski PVT

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The Rogozarski PVT (Рогожарски ПВТ in Serbian, translated as Rogozarski PWT in German and as Rogojarsky PVT in some older English sources) was a single-engined, two-seat parasol winged aircraft designed as an advanced and fighter trainer in Yugoslavia before World War II.

In about 1933 the Rogozarski team of Rudolf Fizir, Sima Milutinović, Kosta Sivčev and Adem Biščević designed the PVT, a training aircraft with tandem open cockpits in an oval wooden monocoque fuselage. Its wooden, canvas covered wings were swept and parasol mounted well above the fuselage with pairs of lift struts to the lower fuselage and a central inverted V cabane. They carried long narrow chord ailerons, with prominent spades well clear of the upper surfaces

Sixty-one were built between 1935 and 1941, serving with the Yugoslav Royal Air Force until the fall of Yugoslavia in 1941. After that, some PVTs were used by the newly formed Croatian Air Force, sometimes as ground attack aircraft.

One PVT was converted to a PVT-H interim seaplane trainer. Three new PVT-H were built in 1937.

Engine: 1 × Gnôme-Rhône 7K, 310 kW (420 hp)
Wingspan: 11.20 m (36 ft 9 in)
Wing area: 22.1 sq.m (238 sq ft)
Length: 8.54 m (28 ft 0 in)
Height: 2.81 m (9 ft 3 in)
Empty weight: 967 kg (2,132 lb)
Gross weight: 1,213 kg (2,674 lb)
Maximum speed: 240 km/h (150 mph; 130 kn) at sea level
Service ceiling: 7,000 m (22,966 ft)
Rate of climb: 6.54 m/s (1,287 ft/min) to 2,000 m (6,562 ft)
Crew: 2