The first all glassfibre SZD type being the prototype Open Class SZD-38 Jantar-1 single-seater (or Amber) of 19m span, designed by Dipl-lng Adam Kurbiel, which first appeared in public at the 1972 World Championships at Vrsac, Yugoslavia, where it came 3rd in the Open Class and won the OSTIV cup for the best 19m design.

In 1972 it set up seven new Polish national records. It was then developed by Dipl-lng W.Okarmus into the SZD-41A Jantar Standard. The T-tailed 19 m. Jantar 1 (SZD 38A) was followed by the 20.5 m. Jantar 2 and 2B versions (SZD 42A) in 1976, which reverted to a conventional tail, and raised the wing to the shoulder position. All models have airbrakes on upper and lower wing surfaces and an unusual upper wing skin consisting of one unbroken sheet all the way to the flap trailing edge, the flaps moving from +8 to -8 degree by bending the skin. Apart from some plywood bulkheads and a welded steel tube fuselage center section carry through, the ship is all fiberglass.

Originally designated SZD-42A, the SZD-42-1 Jantar 2 high performance Open Class single-seater was developed by Dipl-lng Adam Kurbiel from the all-plastics SZD-38A Jantar-1 of which a small number had been built; the Jantar 2 made its first flight on 2 February 1976. The first two prototypes were flown by the Polish team in the 1976 World Championships in Finland, where they came 2nd and 3rd in the Open Class flown respectively by J. Ziobro and H.Muszczynski. These two Jantars had wings built in two sections whereas the production aircraft have the wings built in four pieces for ease of rigging and trailer transport; one of the latter aircraft, flown by R.Johnson of the USA, came 7th in the Open Class in the 1976 World Championships.

Altogether 23 Jantar 2s had been built by the beginning of 1979, and these differ from the Jantar Standard chiefly in having wings of 20.5m (67ft 3in) span and a low-set tailplane with elevators and no tabs. Up to 287lb of water ballast can be carried, and when it is the g limits of the airframe are +4.0/-1.5, or +5.37-2.65 g without the water ballast. The Jantar 2 is of all glassfibre construction very similar to the Jantar Standard; unlike the latter it has hingeless trailing edge flaps hung from the upper surfaces, as well as light alloy DFS-type air brakes in both the upper and lower wing surfaces. The cantilever tail unit is of glassfibre/epoxy resin and there is a retractable monowheel and a tailskid instead of a tailwheel.

A later version was the SZD-42-2 Jantar 2B, which is very similar to the Mk 2 but with the wings raised from the mid to the shoulder position and the incidence reduced slightly. Up to 375lb of water ballast can now be carried, and the Jantar 2B features improvements to cockpit comfort, the monowheel retraction system and the elevator spring trim; there is provision for a towing hook on the cg. The Jantar 2B made its first flight on 13 March 1978 and 32 had been built by the beginning of 1980.

PZL Bielsko / SZD SZD 38 Jantar
Length: 23.622 ft / 7.2 m
Wingspan: 62.336 ft / 19.0 m
Aspect ratio: 27.0
Wing area: 144.022 sq.ft / 13.38 sq.m
Max take off weight: 1146.6 lb / 520.0 kg
Weight empty: 639.5 lb / 290.0 kg
Max. weight carried: 507.2 lb / 230.0 kg
Max. speed: 135 kts / 250 km/h
Landing speed: 35 kts / 65 km/h
Cruising speed: 52 kts / 97 km/h
Wing loading: 8.0 lb/sq.ft / 39.0 kg/sq.m
Glide ratio: 47.0
Crew: 1

Jantar 2
Span: 67 ft 3 in
Length: 23 ft 4 in
Height: 5 ft 9.25 in
Wing area: 153.4 sqft
Aspect ratio: 29.5
Empty weight: 727 lb
Max weight: 1,307 lb
Max speed: 155 mph (in smooth air)
Max aero-tow speed: 87 mph
Min sinking speed: 1.80 ft/sec at 56 mph
Best glide ratio: 48:1 at 63.5 mph

PZL Bielsko / SZD SZD 42 Jantar 2a
Length: 23.327 ft / 7.11 m
Wingspan: 67.257 ft / 20.5 m
Aspect ratio: 29.2
Wing area: 153.279 sq.ft / 14.240 sq.m
Max take off weight: 1278.9 lb / 580.0 kg
Max. speed: 135 kts / 250 km/h
Landing speed: 35 kts / 65 km/h
Cruising speed: 49 kts / 90 km/h
Wing loading: 8.41 lb/sq.ft / 41.0 kg/sq.m
Glide ratio: 48.0
Crew: 1

SZD 42 Jantar 2B
Wing span: 20.5 m / 67.2 ft
Wing area: 14.27 sq.m / 153.6 sq.ft
Aspect ratio: 29.5
Airfoil: Wortmann FX 67-K-150 root
Empty Weight: 362 kg / 798 lb
Payload: 287 kg / 632 lb
Gross Weight: 649 kg / 1430 lb
Wing Load: 45.6 kg/sq.m / 9.28 lb/sq.ft
Water Ballast: 191 kg / 420 lb
L/DMax: 48 90 kph / 49 kt / 56 mph
MinSink: 0.46 m/s / 1.5 fps / 0.89 kt
Seats: 1
No. Built: 60

Jantar 2B
Wing span: 20.15 m / 66 ft l/4 in
Length: 7.11 m / 23 ft 4 in
Height: 1.56 m / 5 ft 1.5 in
Wing area: 14.25 sq.m / 153.4 sq.ft
Wing section: Wortmann FX-67-K-170/150
Aspect ratio: 29.2
Empty weight: 355 kg / 783 lb
Max weight: 645 kg / 1,422 lb
Water ballast: 170 kg / 375 lb
Max wing loading: 45.3 kg/sq.m / 9.28 lb/sq.ft
Max speed: 151 kt / 280 km/h
Stalling speed: 35 kt / 65 km/h
Min sinking: 0.45 m/sec / 1.48 ft/sec at 40.5 kt / 75 km/h
Max rough air speed: 108 kt / 200 km/h
Best glide ratio: 48 at 57 kt / 105 km/h

Adam Kurbiel, the 36-year old designer of the Jantar, started in 1969 and it first flew on 14 February 1972. It was the first Polish glassfibre and GRP.

The Jantar headrest, backrest and pedals are all adjustable in the air and all controls are pushrod operated.

The T-tail is fixed and has a spring trim lever on the side of the control column. Flaps and ailerons work in conjunction and water ballast tanks are fitted.

At least two 19m span were built, plus two with a span of 17.5m. Production plans were in the preliminary stages.

Jantar
Wingspan: 19m
Wing section: FV K67-170-150
Wing area: 13.38 sq.m
Aspect ratio: 27
Empty weight: 275 kg
AUW: 490 kg
Wing loading: 36 kg/sq.m
Min sink: 0,5 m/sec at 75 kph
Stall: 65 kph
Max speed: 250 kph
Glide ratio: 47-1 at 95 kpg

The SZD-36 high performance Standard Class single-seater was designed by Dipl-lng Wladislaw Okarmus for the Polish gliding team at the 1970 World Championships at Marfa, Texas. Design work began in October 1968 and the prototype Cobra 15 made its maiden flight on 30 December 1969. At the 1970 World contest, Jan Wroblewski and Franciszek Kepka of the Polish team flew their early pro¬duction Cobra 15s into 2nd and 3rd places respectively in the Standard Class, and a Cobra 17 – this being the 17m span version – came 5th in the Open Class.

Of all-wood construction with plywood and glassfibre covering, the Cobra 15 has cantilever single-spar shoulder wings with heavy moulded plywood stressed skin covered by glassfibre; the plain ailerons are mass balanced and are of plywood/polystyrene/foam sandwich construction, and there are SZD doubleplate metal glassfibre air brakes in the upper and lower wing surfaces. 45 degree to 45 degree roll rate is less than three seconds. The SZD-39 Cobra 17 is the same as the Cobra 15 except for the increased span (55ft 9.25in) Wortmann profile wing of 23.56 aspect ratio, which has provision for water ballast. The fuselage is an oval section semi-monocoque covered with plywood over the rear part and glassfibre on the forward portion, and there is an aero-tow hook in the lower fuselage forward of the monowheel.

The SZD-36A differs from the SZD-36 in having this hook repositioned about 1 m further forward of the cg with provision for locating it at the cg if required. The monowheel retracts mechanically to lie horizontally in the bottom of the fuselage, and has a brake; there is also a tailskid. The Cobra is distinguished by a sharply swept back fin and rudder with an all-moving mass-balanced tailplane mounted on top of it, with a trim tab on its trailing edge. The pilot sits under a vacuum-formed jettisonable flush-fitting canopy which slides forward to open; there is a small luggage compartment behind the pilot’s seat and also a full range of instrumentation, plus provision for an oxygen system with a 4-litre cylinder in the baggage compartment and a radio.

Altogether 238 Cobras of all versions had been built when production ended in 1977, and the type has been exported to more than 20 countries.

Cobra 15
Wing span: 15 m / 49 ft 2.5 in
Wing area: 11.6 sq.m /124.9 sq.ft
Aspect ratio: 19.4
Length: 7.05 m / 22 ft 11.25 in
Height: 1.59 m / 5 ft 2.25 in
Empty Weight: 257 kg / 567 lb
Payload: 128 kg / 282 lb
Gross Weight: 385 kg / 849 lb
Water ballast: None
Wing Load: 33.2 kg/sq.m / 6.8 lb/sq.ft
Max speed: 155 mph / 135 kt / 250 km/h (in smooth air)
Max rough air speed: 91.5 kt / 170 km/h
Stalling speed: 36 kt / 67 km/h
L/DMax: 38 @ 94 kph / 51 kt / 59 mph
MinSink: 0.60 m/s / 1.97 fps / 1.17 kt at 45.5 mph / 39.5 kt / 73 km/h
Airfoil: Wortmann FX61-168/60-1261
Seats: 1

The SZD-29 Zefir 3 was a much improved version of the SZD-19-2 Mk 2 intended for advanced competition flying, with a wing of 19m (62ft 4in) span, full-span Fowler flaps, a longer fuselage and an unswept fin and rudder; the Mk 3 first flew in prototype form in April 1965 and had an improved best glide ratio of about 42:1.

Its production development was the Zefir 4, the first Mk 4 prototype making its maiden flight on 7 December 1967. It was devleoped for the 1968 World Championships, in which one flown by Jan Wroblewski came 14th in the Open Class.

The wing has an NACA 66-series section and no dihedral, unlike the Mk 2’s; it is a multi-longeron sparless stressed skin wooden structure with full-span flaps like the Mk3’s, the outer sections of which are wooden and also act as ailerons while the inboard sections are of plywood/balsa sandwich; unlike the Mk 2, double metal air brakes are featured. The fuselage is an oval section monocoque, the forward part being made of glassfibre laminate and the rear portion of wood. The tailplane is an all-moving mass-balanced surface with trim tab, and the unswept rudder is also mass-balanced. The monowheel is manually retractable with rubber shock absorbers and a hand-operated wheel brake and, like the Mk 2, a tail-braking parachute is fitted; unlike the Mk 2, the cockpit canopy is now sideways hinging.

Zefir 4
Span: 62 ft 4 in
Length: 26 ft 3 in
Height: 7 ft 0 in
Wing area: 169 sqft
Aspect ratio: 23.0
Empty weight: 772 lb
Max weight: 970 lb
Max speed: 149 mph (in smooth air)
Max aero-tow speed: 93 mph
Min sinking speed: 1.97 ft/sec at 58 mph
Best glide ratio: 42:1 at 58.5 mph

Soaring plane, Poland, 1965

The SZD-25 high performance single-seater combines the wings of the SZD-22 Mucha Standard with a metal fuselage developed from that of the SZD-16 Gil prototype. Designed for large scale production, with low manufacturing and maintenance costs, the Lis (or Fox) made its first flight as a prototype on 5 March 1960, and production aircraft began to enter service with the Polish gliding clubs early in 1962; not a great many were built, but several were exported.

Slotted ailerons are fitted, instead of the SZD-22’s Frise-type ones, and these are aerodynamically and mass balanced, and air brakes are also fitted. The all-metal fuselage is built in two portions: the welded steel tube forward part with fabric covering and the tail boom of riveted sheet duralumin, the cantilever all-wood tail unit being fabric-covered. Landing gear consists of a semi-retractable sprung monowheel with brake and a rubber-mounted nose skid. The pilot sits under a sideways-hinging canopy.

Some 30 were built.

PZL Bielsko / SZD 25 A Lis
Wingspan: 49 ft 2 in / 15.0 m
Wing area: 137.24 sqft
Aspect ratio: 17.65
Length: 23 ft 0 in / 7.0 m
Height: 5 ft 0 in / 1.5 m
Empty weight: 452 lb
Max take off weight: 751.9 lb / 341.0 kg
Max. speed: 124 kts / 230 km/h / 143 mph (in smooth air)
Min sinking speed: 2.5 ft/sec at 43 mph
Glide ratio: 27.0 at 47 mph
Crew: 1

Appropriately named Foka (or Seal), this high performance Standard Class single-seater was designed by Dipl-lng Wladislaw Okarmus and Mynarski, and first flew in prototype form on 2 May 1960.
Flown by Adam Witek, the Foka gained 3rd place in the Standard class in that year’s World Championships at Koln-Butzwerhof, Germany, where the type’s design features aroused interest.

Three pre-production aircraft designated SZD-24B Foka 2 were completed early in 1961, and the first major production variant was the SZD-24C Foka 4 Standard, which first flew in September 1961; deliveries to the Polish gliding clubs and to export customers began soon after. A Foka 4, flown by Jan Wroblewski, won the Open Class at the 1965 World Championships at South Cerney, England.

This version was succeeded in production by the SZD-24-4A (or SZD-24D) Foka 4, which first flew in prototype form in February 1962 and later took part in the 1963 World Championships in Argentina. The Mk4 had the same fuselage as the Foka-Standard but the wing structure was redesigned to make it much simpler and less costly to produce while retaining the same aerodynamic shape.

The first production Foka 4A made its first flight on 7 Feburary 1964 and four Mk4As were flown by the Polish team in the 1965 World Championships at South Cerney, Gloucestershire; in one of these Jan Wroblewski won the Open Class and his team-mate E. Makula came 4th, while the Fokas flown by F. Kepka and J. Popiel took 3rd and 4th places in the Standard Class.

Of all-wood construction, the Foka 4A has two-piece cantilever shoulder wings which are sparless torsion box structures with thick plywood sandwich stressed skin covering which replaces the Foka-Standard’s plywood and foam skinning; the letter’s wing had a central torsion box structure built up of a main spar and two auxiliary spars. There are special SZD plain ailerons of NACA 4415 section. No flaps are fitted but there are SZD metal air brakes at the 60% chord line. The wooden monocoque fuselage is unusual in that the forward part has a modified laminar section, with the maximum depth aft of the pilot’s cockpit at 40% wing root chord; the forward section is covered with a plywood/glassfibre sandwich skin. The pilot sits in a fully-reclining seat under a large flush-fitting canopy which slides forward to open; blind flying instrumentation is standard and there is provision for radio and oxygen. The landing gear consists of a long skid under the nose and a non-retractable monowheel located well aft of the eg, plus a tail bumper. The swept fin is integral with the fuselage and, like the tailplane, is an all-wooden sandwich structure; the laminar flow tailplane and elevator slot into the rear fuselage cone below and behind the rudder in a manner very similar to the Zefir 2. The elevator and rudder are fabric-covered and there is a trim tab in the former.

Final production version was the SZD-32A Foka 5 (formerly SZD-24E), which first flew in prototype form on 28 November 1966 and received its Polish C of A on 7 October 1967; this differed from the Mk 4 chiefly in having a roomier cockpit and the one-piece wooden tailplane and elevator repositioned at the top of the fin. The Foka 5 won first prize at the 1968 OSTIV Congress for the best Standard Class sailplane and a Mk 5 flown by Eward Makula finished 8th in the Standard Class in that year’s World Championships at Leszno, Poland.

The Foka 5 had several other changes from the Mk 4: the wing section was slightly different and the plywood-covered wing was now a multi-longeron semi-monocoque structure, with spars in the inboard section of each panel only; ailerons and air brakes were the same. The fuselage is now a semi-monocoque of oval section, with the monowheel relocated to be under the eg when the aircraft is empty; its brake is linked with the air brakes and the nose skid is retained. The cockpit canopy is slightly shorter but the pilot has the same blind flying instrumentation and provision for radio and oxygen as on the Mk 4.

Altogether 330 Fokas of all variants had been built when production of the type ended in 1971, and 200 of these were exported to 17 countries.

Gallery

PZL Bielsko / SZD 24 Foka
Length: 22.966 ft / 7.0 m
Height: 4.593 ft / 1.4 m
Wingspan: 49.147 ft / 14.98 m
Aspect ratio: 18
Wing area: 130.89 sq.ft / 12.16 sq.m
Max take off weight: 710.0 lb / 322.0 kg
Weight empty: 522.6 lb / 237.0 kg
Max. weight carried: 187.4 lb / 85.0 kg
Max. speed: 140 kts / 260 km/h
Landing speed: 38 kts / 70 km/h
Cruising speed: 51 kts / 94 km/h
Wing loading: 5.33 lb/sq.ft / 26.0 kg/sq.m
Glide ratio: 35.0
Crew: 1

SZD-24C Foka
Wing span: 15m / 49.2ft
Wing area : 12.2sq.m / 131.3sq.ft
Aspect ratio:18.5
Empty Weight: 245kg / 540lb
Payload: 141kg / 311lb
Gross Weight: 386kg / 851lb
Wing Load: 31.64kg/sq.m / 6.48lb/sq.ft
Seats: 1
Airfoil: NACA 63(3)-618, 4415 mod.
L/DMax:34 @ 87 kph / 47 kt / 54 mph
MinSink: 0.67 m/s / 2.2 fps / 1.30 kt
No. Built: 350
Structure: wood, ply/ plastic sandwich skins

Foka 4
Wing span: 15.0 m (49 ft 2 in)
Length: 7.0 m (22 ft 11.5 in)
Wing area: 12.2 sq.m (131.3 sq.ft)
Wing section: NACA 63 3618/4415
Aspect ratio: 18.5
Empty weight: 245 kg (540 lb)
Max weight: 386 kg (851 lb)
Water ballast: None
Max wing loading: 31.64 kg/sq.m (6.48 lb/sq.ft)
Max speed: 140 kt (260 km/h)
Stalling speed: 33.5 kt (62 km/h)
Min sinking speed: 0.7 m/sec (2.3 ft/sec) at 43 kt (79 km/h)
Max rough air speed: 86 kt (160 km/h)
Best glide ratio: 34 at 51 kt (95 km/h)

PZL Bielsko / SZD 32 Foka 5
Length: 23 ft 6.5 in / 7.2 m
Wingspan: 49 ft 2 in / 15.0 m
Aspect ratio: 18.5
Wing area: 131.321 sq.ft / 12.2 sq.m
Height: 5 ft 3.5 in
Max take off weight: 850 lb / 385.0 kg
Weight empty: 564.5 lb / 256.0 kg
Max. weight carried: 284.4 lb / 129.0 kg
Max. speed: 135 kts / 250 km/h / 155 mph (in smooth air)
Landing speed: 37 kts / 68 km/h
Cruising speed: 46 kts / 86 km/h
Min sinking speed: 2.03 ft/sec at 48 mph
Wing loading: 6.56 lb/sq.ft / 32.0 kg/sq.m
Best glide ratio: 36.3:1 at 53mph
Crew: 1

The SZD-22 Mucha Standard Standard Class single-seater had its origins in the IS-2 Mucha (or Fly) intermediate single-seater of 1948. The first Mucha was designed by Nowakowski, Grywacz and Zatwarnicki in 1948 under the auspices of the Polish Gliding Institute, formed in 1946 at Bielsko-Biala. The Mucha-ter was developed into the SZD-12 Mucha 100 of 1953, this single-seater being used for training. It was of all-wood construction, the cantilever high wings having a single main spar and an oblique auxiliary spar, with a plywood-covered leading edge torsion box; air brakes were fitted and the ailerons were aerodynamically and mass balanced. The oval-section fuselage was plywood-covered and the pilot sat under a one-piece Plexiglas canopy. Landing gear consisted of a monowheel and short front and rear skids sprung with rudder pads.

The SZD-22 Mucha Standard was a further development of the Mucha 100 designed by R.Grzywacz espeically for the 1958 World Championships held at Leszno in Poland and, flown by Adam Witek, came 1 st in the Standard Class section of this event. The next year it entered quantity production as a replacement for the Mucha 100 and the SZD-8 Jaskolka and over 150 were built in several versions.

The SZD-22B had a plywood-covered wing and the SZD-22C, which first flew in 1958, a fabric-covered one, the type having the same all-wood construction with a single main spar and an oblique auxiliary spar as the Mucha 100; air brakes were fitted in the upper and lower surfaces, and the fabric-covered Frise ailerons were aerodynamically and mass balanced. The Mucha Standard was one of the first production sailplanes to have provision for water ballast, which was carried in rubber tanks in the inboard leading edge. The fin and rudder differ from the Mucha 100’s in having a squared-off top and a straight trailing edge. The plywood-covered oval-section fuselage had a very similar landing gear to the Mucha 100’s, with a monowheel and front and rear rubber-sprung skids; the SZD-22D had a modified skid and monowheel and the last variant, the SZD-22E, introduced a new wing. The pilot sits under a streamlined clamshell Plexiglas canopy and is provided with a collapsible chart table as well as the conventional insturments; an oxygen installation can also be fitted.

A special experimental high altitude version of the Mucha Standard was also developed, with the cockpit modified for flights at heights above 39,000ft.

Up to 1962, 286 were built.

Mucha Standard
Wing span: 14.98 m / 49 ft 1 in
Length: 7.0 m / 22 ft 11.5 in
Wing area: 12.75 sq.m / 137.3 sq.ft
Wing section: Gottingen 549
Aspect ratio: 17.6
Empty weight: 240 kg / 529 lb
Max weight: 350 kg / 772 lb
Water ballast: None
Max wing loading: 25.6 kg/sq.m / 5.24 lb/sq.ft
Max speed: 135 kt / 250 km/h
Stalling speed: 32 kt / 59 km/h
Min sinking speed: 0.73 m/sec / (2.4 ft/sec at 38.5 kt / 71 km/h
Max rough air speed: 108 kt / 200 km/h
Best glide ratio: 27.8 at 40.5 kt / 75 km/h

SZD 22C Mucha Standard
Wing span: 15m / 49 ft 2 in
Wing area: 12.73 sq.m / 138.2 sq.ft
Length: 23 ft 0 in / 7.0 m
Height: 5 ft 3 in / 1.6 m
Aspect ratio: 17.65
Empty Weight: 240 kg / 530 lb
Payload: 110 kg / 240 lb
Gross Weight: 350 kg / 770 lb
Wing Load: 27.49 kg/sq.m / 6.2 lb/sq.ft
L/DMax: 28 @ 76 kph / 41 kt / 47 mph
MinSink: 0.73 m/s / 2.4 fps / 1.42 kt at 44 mph
Max. speed: 135 kts / 250 km/h / 155 mph (in smooth air)
Seats: 1
Airfoil: Go 549, M 12
Structure: wood/ fabric wings and tail, wood fuselage

Developed between 1958 and 1964, and one of the very few sailplanes designed especially for aerobatics, this high performance single-seater first flew in prototype form as the SZD-21-2 Kobuz 2 on 3 June 1961, and was designed by Trzeciak. lt was developed into the Kobuz 3, the prototype of which was built at the No 4 ZSLS (Sport Aviation Equipment Plant) at Wroclaw, and flew for the first time on 10 December 1964, piloted by S.Skrzydlewski.
An initial production batch of three Kobuz 3s followed in 1965. The Kobuz 3 differed from the Mk 2 in having the cockpit moved forward and the pilot in a semi-reclining instead of a fully reclining seat, a slightly longer and more pointed nose, a wing of 0.5m greater span with plywood stressed-skin covering, and a taller fin and rudder with the low-set tailplane moved back to underneath the rudder. The Kobuz 3 is stressed to airframe limits of + 7G to -5G, and has a cantilever mid-set laminar flow wing built as a sparless torsion box structure with plywood and foam sandwich skinning; the two section ailerons are fabric-covered and flaps as well as air brakes are featured. The monocoque fuselage is built in two portions and is covered with a glassfibre and plywood skin; the cockpit has provision for an oxygen installation and R/T radio. A manually-retractable monowheel is fitted, plus a tail bumper. The cantilever tail unit is structurally similar to the wing, and has a fabric-covered rudder and elevators.

SZD-21-2B Kobuz3
Wingspan: 45 ft 11.5 in / 14.0 m
Wing area: 145.3 sqft
Aspect ratio: 14.52
Length: 23 ft 7.5 in / 7.3 m
Height: 6 ft 3 in / 1.9 m
Max take off weight: 884.2 lb / 401.0 kg
Max. speed: 108 kts / 200 kph
Glide ratio: 30.0
Crew: 1