Designed by Rudolf Kaiser, this single-seater Club Class sailplane was intended as a type on which pilots can progress from the first solo stage to their early competition flights, and is based on the earlier and popular Ka 6E and Ka 8, embodying the docile handling characteristics, simple and rugged construction, soaring ability in weak thermals and good cross-country performance of these types.

The single spar wooden wing has the same aerofoil section as the Ka 6E and a very similar plan form; there are Schempp-Hirth air brakes above and below the wing, the rear part of which is fabric-covered and the ailerons are plywood-covered. The cantilever wooden tail unit has a ply-covered fin and tailplane and fabric-covered rudder and elevators; there is a Flettner trim tab in the elevator. The fuselage, like that of the Ka 8B, is a welded steel tube framework with spruce longerons, and covered overall with fabric; the nose portion is of glassfibre. The pilot sits in a semi-reclining position under a hinged one-piece blown Plexiglas canopy that gives excellent all-round visibility. There is a fixed monowheel just ahead of the c of g with an internal brake, together with a sprung tailskid, and there is no nose skid.

Of similar basically all-wood construction to the Ka 6E and Ka 8, the AS-K 18 first flew in prototype form in October 1974.

No. Built: 48

Schleicher AS-K 18
Wing span: 16 m / 52 ft 5.75 in
Wing area: 12.99 sq.m / 139.8 sqft
Aspect ratio: 19.71
Airfoil: NACA63618/Joukowsky 12%
Length: 22 ft 11.5 in / 7.0 m
Height: 5 ft 6 in / 1.68 m
Empty Weight: 215 kg / 474 lb
Gross Weight: 335 kg / 739 lb
Water ballast: None
Max wing loading: 23.0 kg/sq.m / 4.71 Ib/sq.ft
Max speed: 124 mph / 108 kt / 200 km/h
Max rough air speed: 108 kt / 200 km/h
Stalling speed: 32.5 kt / 60 km/h
L/DMax: 33 at 75 kph / 46.5 mph / 40.5 kt
MinSink: 0.62 m/s / 2 ft/sec at 70 kph / 40.5 mph / 35 kt
Seats: 1

Also known as the Super Orchidee, this Open Class high performance single-seater was designed by Dipl-lng Gerhard Waibel as a development of the AS-W 12. It was the second of Waibel’s Open Class designs.

Superseding the ASW-12, it is a shoulder wing monoplane with a 90 metre wingspan which is in four sections, only 4.5 inches deep at the root. It has a fibreglass span skin, while the fuselage is monocoque two-skin glass fibre sandwich of a special plastic hexcell monocoque. It is dominated by the large dorsal fin and rudder, which is over 6 ft high, which is sculptured from a 6 inch diameter fuselage where the empennage (conventional low-set tailplane and elevator) emerges. The mainplanes have full length four-position flap/ ailerons which give a variable wing geometry of from +9 deg to –11 deg.

The modified Wortmann wing section is thicker than the AS-W 12’s to enable water ballast to be carried in wing tanks. Built in the wings forward of the spar are rubberised ballast tanks with a capacity of 95 litres / 100 kg / 220 lb. For penetration, this load can be dumped in 1 min 50 secs. The aluminum double segment dive brakes in both the upper and lower surfaces are effective to the extent that the tail parachute used in the prototype is no longer a standard item. The single, retractable sprung mono landing wheel is a large 500 x 15, with considerable ground clearance. The wheel brake is operated by a T-bar alongside the left leg. Cockpit space is ample and lengthy, and a pilot up to 6 ft 6 ins can be accommodated quite easily in a semi-reclining seat under a flush-fitting one-piece canopy. Controls are conventional. Ventilation is drawn from the fuselage near the trailing edge. Visibility is excellent, comfort good, and all control reaches are very good.

It first flew in prototype form on 17 July 1971 and 52 AS-W 17s had been built by January 1977; production has now ceased.

The AS-W 17 soon made its mark in competition flying, coming second in the Open Class in the 1972 World Championships at Vrsac, Yugoslavia, flown by Mathias Wiitanen of Finland, third in the 1974 World Championships at Waikerie, Australia, flown by Hans-Werner Grosse of Germany, and winning the 1976 World Championships, held in Finland, for Britain flown by George Lee; this was the first British victory since 1952. The AS-W 17 has made some notable long distance flights, inlcuding a world record goal flight of 765.4 miles by Hans-Werner Grosse on 16 April 1974; he also set a triangular distance record of 660.5 miles (1,063km) in Australia in an AS-W 17 on 18 January 1977, this flight also breaking the speed record for a 1,000km triangular closed circuit at 61.2mph. An ASW-17 flown by Hans Werner Grosse of Germany gained the World record 1,000 km speed triangle at 145.33 kph/ 78.5 kt/ 90 mph and the 1,250 speed triangle at 133.24 kph/ 71.9 kt/ 82.8 mph in 1980.

ASW-17
Wing span: 20m / 65 ft 7.5 in
Wing area: 14.86 sq.m / 159.8 sq.ft
Wing section Wortmann FX-62-K-131 (modified)
Aspect ratio: 27
Length: 24 ft 9.25 in / 7.55 m
Height: 6 ft 1.25 in / 1.86 m
Empty Weight: 404 kg / 890 lb
Payload: 166 kg / 367 lb
Gross Weight: 570 kg / 1257 lb
Water ballast: 100 kg / 220 lb
Max airspeed: 130 kt / 149 mph / 240 km/h (in smooth air)
Rough air speed: 130 kt / 240 km/h
Stall: 37 kt / 68 km/h
L/DMax: 100 kph / 54 kt / 62 mph at 42 kt
MinSink: 0.50 m/s / 1.64 fps / 0.97 kt at 46.5 mph / 40.5 kt / 75 km/h
Best glide ratio: 48.5:1 at 65 mph / 56.5 kt / 105 km/h
Wing Load: 38.36kg/sq.m / 7.8lb/sq.ft
Water ballast: 220 lb
Seats: 1

This high performance Standard Class single-seater was designed by Dipl-lng Gerhard Waibel, and is of glassfibre/foam sandwich construction, it has an all-moving horizontal tail and metal airbrakes for glidepath control.

The AS-W 15 resembles the AS-W 12 externally except for an allmoving tailplane set low on the fin, and the cantilever shoulder wings have a glassfibre roving spar and a glassfibre/balsa sandwich torsion box; the Schempp-Hirth air brakes are spring-sealed in separate boxes to preserve the streamlining, and the ailerons are of glassfibre/foam sandwich construction.

The fuselage is a glassfibre/honeycomb sandwich structure, and ease of rigging is ensured by using tongue-fork connections for the wings, secured by two bolts. The tailplane is similar in construction to the wing, while the fin is similar structurally to the fuselage and the rudder has the same structure as the ailerons. The monowheel is retracted manually by means of push-pull rods, and has an internal drum brake. The pilot sits in a semi-reclining seat under a large flush-fitting one-piece canopy, and his rudder pedals are adjustable in flight.

The ASW-15 was Schleicher’s first composite Standard Class design, originally appearing with a fixed wheel and no water ballast in conformity with the then Standard Class rules. It first flew in prototype form in April 1968, and initially had a fixed monowheel and fairing which could be converted into a retractable one for Open Class competitions, but after this requirement was relaxed the retractable wheel became standard.

With the modification of the Standard Class rules to allow water ballast and retractable gear the ASW15B introduced a number of improvements, including a larger monowheel, a strengthened fuselage keel, a larger rudder, a lengthened cockpit and – as an optional ‘extra’ – two 40 litre (38 kg / 83 lb) water ballast tanks; the all-up weight was increased.

The type made its competition debut at the 1968 World Championships at Leszno in Poland, when an AS-W 15 flown by Hans-Werner Grosse of Germany came 10th in the Standard Class.

A total of 447 AS-W 15s of all versions had been built by January 1977, and production has now ended.

In 1976 an AS-W 15B was fitted with a 30hp Wankel KM 27 300cc rotating piston engine by Ing Joseph Vonderau of Fichtel & Sachs System- Technik. In this form it was known as the AS-W 15M, and a 4.4 Imp gallon fuel tank was installed.

Gallery

ASW-15
Wing span: 15m / 49 ft 2.5 in
Wing area: 10.68 sq.m / 118.2 sq.ft
Wing section: Wortmann FX-61-163/FX-60-126
Aspect ratio: 20.45
Length: 6.48 m / 21 ft 3 in
Height: 1.45 m / 4 ft 9 in
Empty Weight: 230 kg / 507 lb
Payload: 178 kg / 393 lb
Gross Weight: 408 kg / 900 lb
Water Ballast: 90 kg / 198 lb
Max speed: 136.7 mph / 119 kt / 220 km/h
Max aero-tow speed: 90 mph / 119 kt / 220 km/h
Stalling speed: 34 kt / 63 km/h
L/DMax: 38 at 89 kph / 48 kt / 55 mph
MinSink: 0.55 m/s / 1.8 fps / 1.46 kt at 45.5mph / 39.5 kt / 73 km/h
Wing Load: 37.11 kg/sq.m / 7.61 lb/sq.ft
Seats: 1

ASW-15B
Wing span: 15m / 49.2ft
Wing area: 10.68sq.m / 118.2sq.ft
Empty Weight: 230kg / 507lb
Payload: 178kg / 393lb
Gross Weight: 453kg / 1000lb
L/DMax: 38 89 kph / 48 kt / 55 mph
MinSink: 38 89 kph / 48 kt / 55 mph
Wing Load: 41.26kg/sq.m / 8.46lb/sq.ft
Water Ballast: 0
Aspect ratio: 20.45
Airfoil: FX 61-163, FX 60-126
Seats: 1

This tandem two-seater training and high performance glider was developed from the earlier Ka 7, likewise designed by Rudolf Kaiser, and has similar swept forward single-spar wooden wings in the mid-set instead of high position, this lowering of the wings allowing a larger one-piece blown Mecaplex canopy, hinged to starboard, to be fitted giving better all-round visibility; other improvements over the Ka 7 include more comfortable seating, while the AS-K 13 has a better performance than the Ka 7.

There are metal Schempp-Hirth air brakes above and below the wing, and the wooden ailerons are fabric-covered. The wings have a forward sweep of 6° at the quarter-chord line and 5° of dihedral; the D-type leading edge torsion box is of plywood and the whole wing is fabric-covered. The fuselage is a welded steel tube structure with spruce stringers and fabric-covered overall, except for the nose, which is of glassfibre; the turtle decking aft of the cockpit canopy is a plywood shell. The cantilever wooden tail unit is plywood-covered, except for the rear part of the rudder and elevators, which are fabric-covered, and there is a Flettner trim tab in the starboard elevator. In later models, a nosewheel was substituted for the skid. Landing gear consists of a non-retractable sprung monowheel with a drum brake, mounted aft of the cg, with a skid under the forward fuselage and a steel tailskid. The pilots have glassfibre seat panels for greater comfort, and adjustable rudder pedals; there is provision for radio and oxygen, and an aero-tow release is fitted in the nose.

It first flew in prototype form in July 1966 and by January 1978 a total of approximately 700 AS-K 13s had been built, with production continuing. The type is also sold in kit form for amateur constructors.

After Schleicher ceased production, the sailplane has been license-built by Jubi GmbH of Oerlinghausen, Germany.

Gallery

Wing span: 16 m / 52 ft 6 in
Wing area: 17.5 sq.m / 188.4 sq.ft
Aspect ratio: 14.6
Airfoil: Gottingen Go 535/ 549
Length: 8.18 m / 26 ft 9.5 in
Height: 1.6m / 5 ft 3 in
Empty Weight: 290 kg / 639 lb
Payload: 190 kg / 418 lb
Gross Weight: 480 kg / 1057 lb
Water ballast: None
Wing Load: 27.43 kg/sq.m / 5.61 lb/sq.ft
L/DMax: 27 at 90 kph / 49 kt / 56 mph
MinSink: 0.81 m/s / 2.65 fps / 1.57 kt at 43.5 mph / 35 kt / 64 km/h
Max speed: 124 mph / 108 kt / 200 km/h (in smooth air)
Stalling speed: 33 kt / 61 km/h
Max aero-tow speed: 87 mph / 76 kt / 140 km/h
Seats: 2

This Open Class single-seater was designed by Gerhard Waibel – hence the ‘W in its designation -as a production development of the Akaflieg Darmstadt D-36 Circe, in the design of which Waibel had also participated, and which had won the 1964 German National championships.

Of glassfibre reinforced plastic/balsa sandwich construction, the AS-W 12 has cantilever shoulder wings of high aspect ratio (25.8) and with full-span camber-changing flaps interconnected with the ailerons. There are no air brakes, and early examples lacked the later added (and at first non- jettisonable) tail chute. The monocoque fuselage is similar in outline to that of the D-36 Circe, and the pilot sits in a semi-reclining position under a long flush-fitting two-piece cockpit canopy. Landing gear consists of a large retractable unsprung monowheel with brake, plus a tailskid, and a small fixed-incidence tailplane and elevators are mounted on top of the fin.

The prototype AS-W 12 was built by Edgar Krȁmer, who made the first flight in it on 31 December 1965, and the type has since achieved a number of important competition victories and record-breaking flights. In 1969 W. Scott of the USA set a new world goal flight record of 600 miles in an AS-W 12, and in 1970 Hans-Werner Grosse of West Germany became one of the few pilots to make a flight of 1,000km (621 miles), also in an AS-W 12; on 25 April 1972 he set a world record for distance in a straight line by flying 907.7 miles. Grosse was also runner up in the Open Class of the 1970 World Championships at Marfa, Texas, in which five of the first nine places in this class were taken by AS-W 12s.

One example belongs to the National Soaring Museum. No. Built: 15

Wing span: 18.3 m / 60 ft 0.5 in
Length: 7.35 m / 24 ft 1.5 in
Height: 5 ft 3.75 in
Wing area: 13.0 sq.m / 140 sq.ft
Aspect ratio: 25.8
Airfoil: Wortmann FX 62-131K mod.
Empty Weight: 290 kg / 640 lb
Payload: 140 kg / 308 lb
Gross Weight: 430 kg / 948 lb
Water ballast: None
Max speed: 124 mph / 108 kt / 200 km/h
Max rough air speed: 54 kt / 100 km/h
Stalling speed: 35 kt / 65 km/h
L/DMax: 47 at 105 kph / 56 kt / 65 mph
MinSink: 0.49 m/s / 1.6 fps / 0.95 kt at 45 mph / 39 kt / 72 km/h
Wing Load: 33.06 kg/sq.m / 6.07 lb/sq.ft
Seats: 1

Designer: Rudolf Kaiser

The Ka 6E had a low-set all-moving tailplane the same (except for the lack of trim tabs) as on the Ka 10, which did not go into production and was a modified Ka 6CR with the tailplane moved to about one-third of the way up the fin. In the spring of 1965, the Ka 10 took part in the World Championships at South Cerney.

No. Built: 12

L/DMax: 32 84 kph
MinSink: 0.70m/s / 71 kph
Seats: 1
Wing span: 15 m
Wing area: 12.53 sq.m
Empty Weight: 210 kg
Gross Weight: 320 kg
Wing Load: 25.54 kg/sq.m
Aspect ratio: 17.96
Airfoil: Wortmann

Designed by Rudolf Kaiser. Structure: Wood. No. Built: 2

Wing span: 12 m
Aspect ratio: 12
Airfoil: Kaiser
Wing area: 12 sq.m
Empty Weight: 136 kg
Gross Weight: 230 kg
Wing Loading: 19.17 kg/sq.m
MinSink: 0.80 m/s / 67 kph
L/DMax: 20 70 kph
Seats: 1

Designed by Rudolf Kaiser, the Ka-8 was derived from the Ka-6 series as a simple single-place sailplane with dive brakes using construction techniques similar to the Ka-7, and is basically a single-seater version of the two-seater Ka 7, simplified for amateur construction from kits. The structure is wood/ fabric wings and tail, steel-tube/ fabric fuselage. Emphasis was on rugged construction, good climbing ability in thermals and good handling characteristics.

The prototype Ka 8 made its first flight in November 1957 and in its original form the Ka 8 had a very small cockpit canopy, the second version had windows in the sides of the cockpit for improved visibility, and the third version, the Ka 8B, has a larger one-piece blown Plexiglas canopy under which the pilot sits.

The cantilever high wings are single-spar structures of pine and plywood, with a plywood leading edge torsion box and fabric covering aft of the spar; their forward sweep is 1°18′ and dihedral is 3°. There are Schempp-Hirth air brakes in the upper and lower surfaces and the wooden ailerons are plywood covered. The cantilever tail unit is of similar construction to the wings, with ply-covered fixed surfaces and fabric-covered rudder and elevators, and a trim tab in the elevator is an optional fitting.

The fuselage is a welded steel tube structure, with fabric overing over spruce longerons and a glassfibre nose cone. There is a non-retractable and unsprung monowheel, with no brake, and a nose skid mounted on rubber blocks in front of it, plus a steel spur at the tail.

The Ka-8B, by far the most numerous variant, has a substantially larger canopy while the Ka-8C features a longer nose, larger main wheel located ahead to the center of gravity and deletion of the larger wooden nose skid resulting in a roomier cockpit.

Karl Striedeck of the U.S. made a 767.0 km / 476.6 miles ridge flight in a Ka-8B to win the world out and return in 1968.

A motor glider conversion of the Ka 8B was offered by LVD (the Flying Training School of the Detmold Aero Club) similar to their conversion of a Scheibe Bergfalke IV known as the BF IV-BIMO, in which a Lloyd LS-400 piston engine mounted in the fuselage drives a pair of small two blade pusher propellers rotating within cutouts in each wing near the trailing edge.

No. Built: 1100+ in three main versions

Ka-8
Wing span: 15m / 49.2ft
Wing area: 14.21sq.m / 153sq.ft
Aspect ratio: 15.9
Airfoil: Go 533/532
L/DMax: 27 72 kph / 39 kt / 45 mph
MinSink: 0.64 m/s / 2.1 fps / 1.24 kt
Empty Weight: 190kg / 418lb
Payload: 120kg / 265lb
Gross Weight: 310kg / 683lb
Wing Load: 21.81kg/sq.m / 4.45lb/sq.ft
Seats: 1

Schleicher Ka 8B
Span: 15.0 m / 49 ft 2.5 in
Length: 7.0 m / 23 ft 0 in
Height: 1.57 m / 5 ft 1.75 in
Wing area: 14.15 sq.m / 152.3 sq.ft
Wing section: Gottingen 533/532
Aspect ratio: 15.9
Empty weight: 190 kg / 419 lb
Max weight: 310 kg / 683 lb
Water ballast: None
Max wing loading: 21.9 kg/sq.m / 4.48 lb/sq ft
Max speed: 124 mph / 108 kt / 200 km/h (in smooth air)
Max aero-tow speed: 81 mph / 70 kt / 130 km/h
Stalling speed: 29 kt / 54 km/h
Min sinking speed: 2.1 ft/sec / 0.65 m/sec at 37.5 mph / 32.5 kt / 60 km/h
Best glide ratio: 27:1 at 45.5 mph / 39.5 kt