I.S.T. L-17

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L-17 Masang
Role Touring and training aircraft
National origin Republic of the Philippines
Manufacturer Institute of Science and Technology, Manila
Designer Antonio J. de Leon
First flight May 1956?
Number built 1?

The I.S.T. L-17 Masang was a two seat, single engine, low wing monoplane aircraft designed and built in the Philippine Republic in the mid-1950s. It was intended for both touring and training.

Design and development[edit]

In the mid-1950s the Philippine Institute of Science and Technology (I.S.T.) designed aircraft to explore the possibilities of local aircraft production from indigenous materials. The single engine, tricycle undercarriage, low wing monoplane L-17 was one of them.[1]

Its wing was a single piece wooden structure with 5° of dihedral and a straight tapered plan. It was plywood covered and had split flaps inboard of the ailerons. The cantilever tail unit was similarly constructed with the straight tapered horizontal surfaces on top of the extreme aft fuselage; the single piece elevator carried an offset trim tab. The vertical tail was tall and straight edged; the bottom of the horn balanced rudder was above the elevator and just aft of its hinge, with a small cut-out to allow for elevator deflection.[1]

The L-17's fuselage was a plywood skinned wooden semi-monocoque, the cockpit seating two side-by-side under a single piece canopy. A 108 hp (80 kW) Lycoming O-235 flat four engine drove a two blade propeller. The fixed tricycle undercarriage had rearward sloping oleo legs mounted to the wings, giving a track of 2.40 m (7 ft 10 in).[1]

The first flight of the L-17 was scheduled for May 1956.[1]

Specifications[edit]

Data from Jane's All the World's Aircraft 1956/7[1] - all performance figures estimated

General characteristics

  • Crew: 2
  • Length: 7.20 m (23 ft 7 in)
  • Wingspan: 9.60 m (31 ft 6 in)
  • Height: 3.20 m (10 ft 6 in)
  • Wing area: 13.40 m2 (144.2 sq ft)
  • Airfoil: US 35B at root, NACA 23012 tip
  • Empty weight: 510 kg (1,124 lb)
  • Gross weight: 735 kg (1,620 lb)
  • Fuel capacity: 68 L (15 Imp gal, 18 US gal)
  • Powerplant: 1 × Lycoming O-235-C1 4-cylinder horizontally opposed, air cooled, 81 kW (108 hp)
  • Propellers: 2-bladed , fixed pitch, wooden

Performance

  • Maximum speed: 210 km/h (130 mph; 113 kn)
  • Cruising speed: 175 km/h (109 mph; 94 kn)
  • Rate of climb: 3.8 m/s (750 ft/min)

References[edit]

  1. ^ a b c d e Bridgman, Leonard (1956). Jane's All the World's Aircraft 1956-57. London: Jane's All the World's Aircraft Publishing Co. Ltd. p. 192.