LIBIS KB-6
title: "LIBIS KB-6" type: doc version: 1 created: 2026-02-28 author: "Wikipedia contributors" status: active scope: public tags: ["libis-aircraft"] topic_path: "general/libis-aircraft" source: "https://en.wikipedia.org/wiki/LIBIS_KB-6" license: "CC BY-SA 4.0" wikipedia_page_id: 0 wikipedia_revision_id: 0
::data[format=table title="Infobox aircraft"]
| Field | Value |
|---|---|
| name | KB-6 Matajur |
| image | BAM-45-Letov KB-6 Matajur.jpg |
| type | Two-seat light basic trainer and touring aircraft |
| manufacturer | LIBIS aircraft (Letalski Inštitut Branko Ivanuš Slovenija) |
| designer | Dušan Cener |
| first_flight | 4 June 1952 |
| status | Retired |
| primary_user | Slovenian aero clubs |
| :: |
|name= KB-6 Matajur |image=BAM-45-Letov KB-6 Matajur.jpg |caption= |type= Two-seat light basic trainer and touring aircraft |manufacturer=LIBIS aircraft (Letalski Inštitut Branko Ivanuš Slovenija) |designer= Dušan Cener |first_flight= 4 June 1952 |introduction= |retired= |status=Retired |primary_user= Slovenian aero clubs |more_users= |produced= |number_built=
The LIBIS KB-6 Matajur was a 1950s Slovenian two-seat light monoplane designed and produced by LIBIS aircraft during Yugoslavian period.
Design and development
The aircraft design office of LIBIS brought together teachers and students of the Ljubljana technical high school. The design office designed the KB-6 Matajur which was a two-seat light trainer and tourer that first flew on 4 June 1952. The KB-6 was a cantilever low-wing monoplane with fixed tailwheel landing gear and an enclosed cockpit with side-by-side seating and dual controls. The aircraft was produced for use in aero-clubs until the mid-1960s.
Variants
;KB-6 Matajur :Main production variant, powered by a 135 hp Regnier 4L.00 inline engine. ;KB-6T Matajur-Trised :Three-seat development powered by a 160 hp Walter Minor 6-III-J inline engine, eight built. ;LIBIS 160 :Further developed version of the KB-6T with swept vertical tail, 11 built.
Specifications (KB-6)
|ref=Jane's All The World's Aircraft 1953-54 |prime units?=met General characteristics
|genhide=
|crew=2 |capacity= |length m=8.36 |length ft= |length in= |span m=10.60 |span ft= |span in= |height m=2.15 |height ft= |height in= |wing area sqm=14.0 |wing area sqft= |aspect ratio=8:1 |empty weight kg=659 |empty weight lb= |gross weight kg=979 |gross weight lb= |fuel capacity=141 L Powerplant
|eng1 number=1 |eng1 name=Régnier 4L.00 |eng1 type=inverted four-cylinder air-cooled inline piston engine |eng1 kw= |eng1 hp=135
|prop blade number=2 |prop name=fixed pitch wooden propeller |prop dia m=1.95 |prop dia ft= |prop dia in=
Performance
|perfhide=
|max speed kmh=222 |max speed mph= |max speed kts= |max speed note=at sea level |cruise speed kmh=200 |cruise speed mph= |cruise speed kts= |stall speed kmh=88 |stall speed note=(flaps down) |range km=820 |range miles= |range nmi= |ceiling m=4500 |ceiling ft= |climb rate ms= |climb rate ftmin=689 |more performance=
|avionics=
Notes
References
References
- Taylor 1964, p.335
- Bridgman 1953, pp. 279–280.
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