Specification of Tatra T-101.1
The Tatra T-101 was an experimental type, designed initially for training purposes. Originally it was to be an alternative to the T–001 aeroplane, with enlarged wings of 13 m span and with a wing area of 16.4m2 . This experimental type was, after its excellent high-altitude and distance flying capabilities were realised, used for height and distance record flights.
The T – 101 was a low wing monoplane, with a glazed cabin and two seats in tandem. The fuselage was of the same style of construction as that of the T–001, and the cabin was extensively glazed. Ventilation louvres were located on the front right side of the canopy, which could be adjusted during flight. Ventilation was also possible through the shifting slots. Waste air regulation was expelled via a vent in the rear fuselage, behind the cabin.
The wing was a cantelever, single spar construction, built as one unit from tip to tip and covered in plywood. The basic design of the spar and ribs was the same as that used on the T-001. The aileron structure was of wood covered with fabric, and they were statically and aerodynamically balanced. Fuel tanks were located in the wing centre-section, forward and aft of the mainspar.
The landing gear comprised two cantilever legs carrying mid–pressure wheels, and were equipped with Tatra shock absorbers, combining spring and hydraulic shimmy damping. The wheels were fitted with mechanical brakes controlled by two independent pedals. The wheel covers could easily be shifted upward to aid landing gear maintenance and wheel changes.The tailwheel was interconnected with the rudder, and was thus steerable through a moderate range, although the pilot could also disengage the steering to allow the wheel to castor freely through 360°.
The tail unit was constructed from chromium-molybdenum tubes and was covered with fabric, in the same fashion as on the T–001. The elevator was aerodynamically and also partially statically balanced. The balance tabs on the trailing edges were wooden, as were those on the T–001. The primary flight controls worked in the conventional ‘stick and rudder’ sense, with the rudder and ailerons being cable operated. Controls were provided in each cockpit, although the control column in the front cockpit was removable.
The T-101 was powered by the four cylinder inverted air–cooled Tatra T–100 engine (power 72 kW (92 h) at 2480 rev/min). Attached to the engine was a Bosh LE 300/12 AL 7 (power 300W, voltage 12 V) dynamo, supplying electric power to the aircraft’s lighting system (essential for operating at night during the distance record flight). The engine mounting was formed of two independent bearers, welded from chromium-molybdenum tubes and set on rubber dampers. The airscrew was usually wooden with a metal leading edge sheath, although for special flights a metal propeller was fitted.
The engine compartment was separated from the cabin by a firewall, made from two duralumin sheets with asbestos in between. The 125 litre fuel tank was placed directly behind the firewall. The fuel was fed from this tank to the engine via a fuel filter and three–way valve, which could be controlled by both pilots. Fuel from left and right wing tanks was piped via a four–way valve, controlled from the back seat, before passing through the same fuel filter to the engine. This four–way valve could control the flow from the fuselage tank and the left or right wing tanks simultaniously. All tanks were filled through the one fuel filler cap in the fuselage tank. The oil tank was placed directly adjascent to the engine.
The whole aeroplane was sprayed with ‘aluminium bronze’, and the trim and emblems of the factory were then added in blue. The registration letters and sundry stencils were painted in black.
|Wing span||13.00 m|
|Wing area||16.40 m2|
|Aeroplane empty weight||500 kg|
|Maximum take off weight for category I.||780 kg|
|Maximum take off weight for distance flights||1100 kg|
|Maximum speed at sea level||215 km/h|
|Cruise speed at 2250 rpm||190 km/h|
|Landing speed||65 km/h|
|Time to climb to 1000 m||5.5 min.|
|Maximum ceiling||5000 m|
|Range at cruise speed||1200 km|
|Max. range for distance flights with full tanks||cca 5000 km|