The Vihuri (Squall) was built for the Finish Air Force by Valmet OY at Tampere. The prototype flew for the first time on 6 February 1951, and the first production machine of an initial batch of thirty was flown on 3 August 1953.
Engine: 820 hp Bristol Mercury 8
Wingspan: 33 ft 1 in
Wing area: 202.9 sq.ft
Length: 28 ft 9 in
Height: 12 ft 8 in
Max weight: 6345 lb
Max speed: 268 mph at 12.140 ft
Econ cruise: 203 mph at 3280 ft
ROC: 2263 fpm
Service ceiling: 29,100 ft
Seats: 2
The Valmet PIK-23 Towmaster is a Finnish two-seat glider towing/primary trainer aircraft built entirely out of composite materials in the early 1980s.
The Finnish technology students aviation club suggested in the 1970s, that a new aircraft should be developed for glider towing. The work focused on the improvement of a previous design, the PIK-19 Suhinu (Suhinu is a contraction of Super Hino = Super Tow-plane). Later on, the Helsinki University of Technology and Valmet Oy joined the project and the design process started from scratch. The goal was to develop a target/glider tower, which also could be used for basic training. It was given the name “PIK-23 Towmaster”.
Only two aircraft were manufactured, one at Valmet and one at the Helsinki University of Technology. The first aircraft, OH-TOW, made its maiden flight on March 22, 1982, flown by Mikko Järvi. The second aircraft, OH-TUG, flew the following year. OH-TUG was written of in 1991.
Valmet marketed the aircraft intensively, but no orders followed. It was also investigated if the aircraft could be sold in parts, for self-assembly, in order to lower the price. In its intended role as a glider tower, the PIK-23 has been quite successful.
PIK-23
Engine: 1 × Avco Lycoming O-360-A4M, 130 kW (180 hp)
Propeller: 2-bladed Hoffmann fixed pitch
Wingspan: 10.00 m (32 ft 10 in)
Wing area: 14.00 m2 (150.7 sq ft)
Aspect ratio: 7.14:1
Airfoil: NACA 632415 (modified)
Length: 7.19 m (23 ft 7 in)
Height: 2.90 m (9 ft 6 in)
Empty weight: 590 kg (1,301 lb)
Max takeoff weight: 870 kg (1,918 lb)
Fuel capacity: 200 L (44 imp gal; 53 US gal)
Maximum speed: 250 km/h (160 mph, 130 kn) at sea level
Cruise speed: 220 km/h (140 mph, 120 kn) at 3,660 m (12,010 ft) (65% power)
Stall speed: 78 km/h (48 mph, 42 kn) (flaps down)
Never exceed speed: 281 km/h (175 mph, 152 kn)
Range: 1,250 km (780 mi, 670 nmi) at 3,660 m (12,010 ft) (65% power)
Endurance: 6 hr 30 min (55% power)
Rate of climb: 5.80 m/s (1,142 ft/min)
Takeoff run to 15 m (50 ft): 320 m (1,050 ft)
Crew: 2
The L.90TP was derived from the earlier L.70 through an intermediate turboprop design known as the L.80TP in 1985.
Own designed Leko-70 Vinka two-seat piston-engined trainer evolved by new design group created September 1970. The L.70 first flew on July 1, 1975.
Valmet L.70 Militrainer Article
30 Valmet Vinka were delivered to the Finish air force in the late 1970s, and entered service as the Vinka in October 1980. Production of the L.70 piston-engined side-by-side primary/basic trainer for the Finnish Air Force ended in 1982.
L-70 Miltrainer
Engine: 1 x Lycoming AEIO-360, 150 kW
Span: 9.8 m
Length: 7.5 m
Wing area: 14.5 sq.m
Empty wt: 765 kg
MTOW: 1250 kg
Warload: 300 kg
Max speed: 235 kph
Initial ROC: 340 m / min
Ceiling: 4800 m
T/O run: 230 m
Ldg run: 175 m
Fuel internal: 170 lt
Range: 970 km
Two-seat trainer designed by engineer Arvo Ylinen. The Finnish Air Force had 22 aircrafts in use in 1937 – 1963, in addition the civilian aircraft OH-ILM was added as VI-40 in 1953.
A Back Yard Flyer UL prototype was built by Valley Engineering in 2005 as a STOL ultralight. Featuring a constant-chord wing with trailing full-length “flaperons.” Demonstrated take-off in about three seconds over 70 feet. With simple disassembly for trailering it was priced around.$25,000.
Planned production was for a two place, open cockpit low wing monoplane, side-by-side SP version for the FAA Part 103 Sport Pliot market, includes ballistic parachute system.
Engine: Valley-VW
Cruise speed: 90 mph
Stall: 30 mph
Seats: 1
Taifun 12E as two-seat lightplane was developed into Taifun 11S four-seater of 1988.
Valentin Flugzeugbau Gmbh developed Taifun 12E as two-seat lightplane (first flown 1985), it has a two bladed non retracting Muhlbauer variable pitch feathering propeller.
Further developed into Taifun 11S four-seater of 1988.
The Taifun two-seater motor glider was designed by Thomas Fischer and Dipl-lng Jorg B. Stieber for Valentin GmbH Gerateund Maschinenbau, makers of high-quality aircraft switches.
The Taifun is a cantilever low wing monoplane with a T-tail; the one-spar wings and ailerons are of glassfibre/foam sandwich construction, with all glassfibre flaps. The wings can be folded flat along the fuselage for easier hangar stowage, and Schempp-Hirth air brakes are fitted in their upper surfaces. The stressed skin fuselage is also a glassfibre/foam sandwich structure as are the fixed incidence tailplane and elevator. All versions have disc brakes on the main wheels, and the nosewheel of the 15E and 17E is steerable; the undercarriage of both these variants is fully enclosed when retracted. The pilots are seated side-by-side under the rear sliding canopy, with dual controls as standard. Engine is an 80hp Limbach L2000 EB ‘flat four’ driving a Hoffman HO-V62 three-position two bladed
propeller.
Construction of the prototype had begun in July 1979. The prototype, a Taifun 17E registered D-KONO, made its first flight late in February 1981, as the Valentin Taifun, when more than 25 had been ordered.
Four versions of the Taifun were to be produced: the Taifun 15S is the basic model with 15m span wings and a fixed tailwheel undercarriage, the Taifun 17S has the same undercarriage as the 15S and 17m span wings, the Taifun 15E has 15m span wings and a retractable nosewheel undercarriage, and the Taifun 17E has the same undercarriage as the 15E but has 17m span wings.
Taifun 15E
Span: 49 ft 2.5 in
Length: 25 ft 6.5 in
Height: 7 ft 1 in
Wing area: 176.0 sqft
Aspect ratio: 13.8
Empty weight: 1,058 lb
Max take-off weight: 1,598 lb
Max speed: 165 mph (in smooth air)
Max cruising speed: 132 mph
Min sinking speed: 3.25 ft/sec at 54 mph
Best glide ratio: 28:1 at 75 mph
Max rate of climb: 531 ft/min at sea level
Range with max fuel: 652 miles
Taifun 15S
Span: 49 ft 2.5 in
Length: 25 ft 6.5 in
Height: 7ft 1 in
Wing area: 176.0 sqft
Aspect ratio: 13.8
Taifun 17E
Span: 55 ft 9.25 in
Length: 25 ft 6.5 in
Height: 7ft 1 in
Wing area: 189.4 sq ft
Aspect ratio: 16.4
Taifun 17S
Span: 55 ft 9.25 in
Length: 25 ft 6.5 in
Height: 7ft 1 in
Wing area: 189.4 sq ft
Aspect ratio: 16.4
TWI Taifun 17E II
Engine: 67 kW/ 90 bhp Limbach L 2400 EB1.b
Wing span: 17 m / 55.7 ft
Wing area: 17.6 sq.m / 189.4 sq.ft
Aspect ratio: 16.4
Airfoil: Wortmann FX-67-K-170/7
Empty Weight: 610 kg / 1345 lb
Payload: 240 kg / 529 lb
Gross Weight: 850 kg / 1874 lb
Wing Load: 48.3 kg/sq.m / 9.9 lb/sq.ft
L/DMax: 30 115 kph / 62 kt / 71 mph
MinSink: 0.95 m/s / 3.12 fps / 1.85 kt
Seats: 2
All Aero 