Jim Maupin of San Pedro, CA offered an inexpensive way to get into the action, with his homebuilt sailplane Woodstock, designed with the philosophy, “Build it light, build it small, build it cheap and simple.” Only basic tools are needed. Woodstocks wing, designed by lrv Culver, is built around a single main spar, formed as a hollow box out 8 feet and as a c-section beyond. Ribs are sawn from ¼-inch fir plywood, glued to the spar fore and aft. Spar runs the full length of the wing. Wing forward of the spar is covered with 1/4 -inch birch ply as a D section. Fuselage and tail are equally simple to build. An info kit was $5, plans $105 ($115 overseas).

Woodstock was designed with a wing having an 18 % section for the root, 13 % at the tip and no twis. The principal design objectives were low cost and simplicity of construction. Douglas Air was used for all major structural parts and all tail and wing skins were birch. It first flew in 1978 and won the Sailplane Homebuilders Association design contest in 1984. A tail wheel is an option instead of a skid. The main wheel is fixed. Approach control is by wing top surface spoilers. As an option, wings of 13.1 m./ 43.0 ft.

Woodstock
Wing span: 11.89 m / 41.5 ft
Wing area: 9.73 sq.m / 104.7 sq.ft
Aspect ratio: 14.5
Airfoil: Culver
Length 5.43 m / 17 ft 10 in
Height: 1.22 m / 4ft 0 in
Empty Weight: 111 kg / 245 lb
Payload: 95 kg / 210 lb
Gross Weight: 206 kg / 455 lb
Water ballast: None
Wing Load: 20.9 kg/sq.m / 4.29 lb/sq.ft
L/DMax: 24 at 72 kph / 39 kt / 45 mph
MinSink: 0.79 m/s / 2.6 fps / 1.54 kt
Seats: 1

Woodstock 15M
Wing span: 15 m / 49.2 ft
Wing area: 10.18 sq.m / 109.6 sq.ft
Height: 3.5 ft
Length: 19 ft
Empty Weight: 111 kg / 245 lb
Payload: 120 kg / 265 lb
Gross Weight: 206 kg / 455 lb
Wing Load: 22.69 kg/sq.m / 4.65 lb/sq.ft
Aspect ratio: 16.8
Airfoil: Culver
Seats: 1
L/DMax: 26.5 72 kph / 39 kt / 45 mph
MinSink: 0.79 m/s / 2.6 fps / 1.54 kt
Stall: 35 mph
Landing gear: single wheel
Load limit 5.0 G

Designed by Jim Maupin and Irv Culver to meet SHA Homebuilt Sailplane Design Contest criteria: easy to built, low cost, soarable, self-launching, safe, the definitive powered Windrose first flew in 1984. The structural backbone is a hollow plywood box with corners longerons which carry the engine mounts, landing gear and fiberglass cockpit shell. The wings are shaped foam covered with fiberglass, but without a conventional spar. The spars are bands of unidirectional roving expoxied into recesses in the upper and lower wing skins, and separated by rows of vertical dowels between the bands to take compression loads off the foam. Ailerons are set inboard from the root to approximately two-thirds span operated by pushrods from the fuselage. The wing structure is free of controls, pushrods, cables etc. Glidepath control is by a triangular spoiler which rises above the wing center section. Both tail surfaces are all-moving. The design comes in 12.65 and 15.0 m models.
Windrose was offered as partial or complete kit, or plans only. Plans used to cost $175 in the US and Canada, airmail overseas for $195.

The Windrose II motor glider has an optional shorter wing span or Cuyuna UL-II-02 engine.

Windrose
Wing span: 12.65 m / 41.5 ft
Wing area: 8.92 sq.m / 96 sq.ft
Aspect ratio: 17.9
Empty weight: 355 lb
Gross weight: 565 lb
Wing loading: 5.93 lb/sq.ft.
Airfoil: Culver
Seats: 1

Windrose
Engine: 25 kW/ 33 bhp Cuyuna ULII-02 / Rotax 503, 46 hp
Wing span: 12.65 m / 41.5 ft
Wing area: 8.92 sq.m / 96 sq.ft
Empty Weight: 177 kg / 390 lb
Payload: 95 kg / 210 lb
Gross Weight: 272 kg / 600 lb
Wing Load: 28.51 kg/sq.m / 6.3 lb/sq.ft
Aspect ratio: 17.9
L/D Max: 29 84 kph / 45 kt / 52 mph
Min Sink: 0.70 m/s / 2.3 fps / 1.36 kt at 46 mph
Airfoil: Culver
Seats: 1

Windrose
Gross Wt. 650 lb
Empty Wt. 440 lb
Wingspan 41’7”
Wing area 95.25 sq.ft
Aspect ratio 18.25 to 1
Wing loading 6.82 lb/sq.ft
Engine 35-hp Cuyuna UL 11-02
Takeoff run, standard day 600 ft
Climb rate 500 fpm @ 52 mph
L/D max 30/1 @ 49 mph
Min sink 2.3 fps @ 41.5 mph.

Windrose 15M
Wing span: 15m / 49.2 ft
Wing area: 9.54 sq.m / 102.66 sq.ft
Empty Weight: 232 kg / 512 lb
Payload: 104 kg / 228 lb
Gross Weight: 336 kg / 740 lb
Wing Load: 37.67 kg/sq.m / 7.7 lb/sq.ft
Seats: 1
L/DMax: 38 82 kph/ 44 kt/ 51 mph
MinSink: 0.56 m/s / 1.85 fps/ 1.10 kt
Aspect ratio: 23.26
Airfoil: Culver
Engine: 34 kW/ 46 bhp Rotax 503

Windrose II
Cruise: 132 mph
Stall: 50 mph
ROC: 700 fpm
Take-off dist: 500 ft
Landing dist: 300 ft
Service ceiling: 13,000 ft
Engine: Rotax 503, 46 hp
Fuel cap: 5 USG
Weight empty: 512 lb
Gross: 740 lb
Length: 21.6 ft
Wing span: 49.2 ft
Wing area: 102 sq.ft
Seats: 1
Landing gear: single wheel

Designed by Jim Maupin & Irv Culver, the Carbon Dragon first flew in 1988. Altrough meeting the FAI definition of a hang glider, the Carbon Dragon can be launched by foot, aerotow, or bungee. Roll control and approach control are by full span 30 % chord flaperons, and at least one has been modified by the addition of a pentagonal shaped spoiler in the wing section, similar to that on the Maupin Windrose. It has a fixed main wheel. It complies with U.S. FAA Part 103 rules. In 1994 it became the first sailplane in that class to win against conventional gliders in a scheduled, non-handicapped cross-country contest.
An ultralight sailplane, basic wood construction with use of carbon epoxy to reduce weight and improve stiffness. Was available as plans for $150. Price (1998) $ 170 (Plans)
Building time estimated at 1500 hours.

Weight: 65 kg / 145 lb
Gross Weight: 151kg / 335lb
Payload: 85kg / 190lb
Wing span: 13.2 m / 44 feet
Wing area: 14.25sq.m / 153.34sq.ft
Vne: 112 km / 70 mph
L/D: 25:1 at 32 mph
Stall: 20 mph
Min sink: 0.51 m/s / 100 fpm / 0.99 kt at 26 mph.
Seats: 1
Wing Load: 10.61 kg/sq.m / 2.18 lb/sq.ft
Aspect ratio: 12.62
Airfoil: Culver CD
Landing gear: single wheel