Kaiser Flugzeugbau DEKO-9 Magic
Dakomat Deko 9 Magic
A single-seat aerobatic sports and recreation biplane, the prototype aircraft developed on order from the German Kaiser-Flugzeugbau GmbH. The construction of the prototype, strength tests and flight tests carried out in Military Aviation Plant No. 3 Deblin (later called the Military Aviation Plant No. 1 SA branch) in Dęblinie, Poland. The design work, construction of prototypes and the necessary infrastructure took from 1996 to 1998.
The team headed by Lt.-Col. MSc. Wieslaw Pochylskiego, established a composites laboratory and strength tests, and a thermal tent enabling the study of metal-composite structures at elevated temperatures. Other members included Dr. Eng. Marek Debski and M. Sc. Christopher Kotliński. Builders and MSc. Marian Jakoniuk, MSc. Witold Wiraszka, Eng. Bruno Biernacki and Dr. Eng. Daniel Debski.
Calculations and strength tests were conducted by M.Sc. Vladimir Urbaniak - load, dr. Andrew Szot, MSc. George Mularczyk - static strength tests, Dr. Eng. Wojciech Hajec, MSc. James Kulecki - model airplane spin research, Warsaw University of Technology.
A biplane, the crew seats in tandem with a one-piece canop, and with a fixed main landing gear and tail wheel. The supporting structure of the fuselage is duralumin tube in composite nodes. The wings are double-girder construction with beams made of duralumin tubes and fixed to them duralowej pressed sheet metal ribs. The tail is welded construction made of thin-walled steel pipes. Polish made aircraft are overed with a heat-shrinkable polyester fabric, Dekonit 140 g / m².
First flight of the aircraft on 30 September 2000 and flight tests were performed by test pilot, MSc. , Maciej Aksler. The aircraft was presented at exhibitions air: ILA Berlin 1998 and 2000 and Fredrichshafen AERO 1999 and 2001.
ILA Berlin 2000
The engine ofsix produced by PZL Rzeszow was the 200 hp PZL Franklin 6A-350C1R , suitable for inverted flight and driving a three-bladed MT-Propeller MTV-9-DC / C188-18a propeller with hydraulically controlled pitch.
Also developed of four-cylinder Franklin 4A-235B4 92 kW (125 hp) powered version with open cockpit.
Engine: PZL Franklin 6A-350C1R, 205 hp (150 kW)
Span: 6.8 m
Length: 6.5 m
Height: 2.2 m
Wing area: 15.4 m²
Empty weight: 500 kg
Useful load: 250 kg
MAUW: 750 kg
Fuel capacity: 100 lt
Max speed: 220 km / h (119 kts IAS)
Cruising speed: 190 km / h (103 kts IAS)
Minimum speed: 90 km / h (49 kts IAS)
Vne: 350 km / h (189 kts IAS)
Rate of climb: 12 m / s (2362 ft / min)
Ceiling: 4000 m (13123 ft)
Range: 700 km (378 nm)
Take-off dist: 120 m (393 ft)
Landing dist: 120 m (393 ft)
Load factor design: + 6 / -3 g