Wassmer WA 22 Super Javelot / WA 23
The Super Javelot is a single-seat Standard Class version of the WA 20 Javelot with three-piece instead of two-piece wings of 15m span and 5° 30' dihedral on the outer panels, there being no dihedral on the centre section; the modified fuselage has the forward portion covered with three resin-bonded glass-cloth panels and the rear part fabric-covered, the nose now being longer and more streamlined and the blown plastic canopy redesigned. In addition, the fin and rudder are now swept back.
The cantilever wooden shoulder wings have single spars and the wooden ailerons are each in two parts operated differentially; there are perforated wooden air brakes above and below each wing, and small end-plate 'bumper'-type fairings at the wing tips. The welded steel tube fuselage framework is now in two portions, the forward section having four longerons and the rear part only three, both sections being differently covered to those of the Javelot. The cantilever tail unit is of wood, with a trim tab in the one-piece elevator. Landing gear consists of a rubber-sprung nose skid with a non-retractable monowheel mounted aft of it; this has a brake linked to the wing air brake control, and there is also a rubber-sprung tailskid. The pilot sits in a canvas seat and there is provision for radio and oxygen.
The prototype Super Javelot first flew on 26 June 1961 and the type succeeded the WA 21 Javelot in production; in 1964 two Supers a month were being turned out.



A number of refinements were introduced on the 1964 model, which was known as the Super Javelot 64; these included a modified leading edge for improved performance at low speeds, modified wing roots to improve airflow at the wing/fuselage junction, increased dihedral of 5° 30' on the outer wing panels and the use of birch plywood to cover the entire wings to give better laminar flow.
The Wassmer WA 23, of which the prototype first flew on 6 August 1962, was an experimental 'one-off' sailplane used to test a new 18m (59ft 0in) span wing with an aerofoil section developed by M Maurice Collard; this had an aspect ratio of 22 and was married to the fuselage of a WA 22 Super Javelot.
Super Javelot 64
Span: 49 ft 2.5 in
Length: 23 ft 2 in
Height: 6 ft 3 in
Wing area: 155.0 sqft
Aspect ratio: 15.7
Empty weight: 452 lb
Max weight: 750 lb
Max speed: 124 mph
Min sinking speed: 2.29 ft/sec at 50 mph
Best glide ratio: 30:1
WA 22 Super Javelot
Wing span: 15.0 m / 49 ft 2.5 in
Length: 7.06 m / 23 ft 2 in
Height: 1.9m / 6 ft 3 in
Wing area: 14.4 sq.m / 155 sq ft
Wing section: NACA 63821 /63615
Aspect ratio: 15.7
Empty weight: 205 kg / 452 lb
Max weight: 350 kg / 750 lb
Water ballast: None
Max wing loading: 24.3 kg/sq.m / 4.84 lb/sq ft
Max speed: 108 kt / 200 km/h
Stalling speed: 33 kt / 61 km/h
Min sinking speed: 0.7 m/sec / 2.29 ft/sec at 43 kt / 80 km/h
Max rough air speed: 70 kt / 130 km/h
Best glide ratio: 30