Aerobatic Aircraft
Staudacher S-300D
1980->
Staudacher Aircraft Inc
USA
Staudacher Aircraft Inc custom-built aerobatic aircraft.
Statler Dos Equis Challenger
The 1982 William H Statler Dos Equis Challenger was a single-place modified North American SNJ-5 as racer in the unlimited class.
Engine: 2100hp P&W R-2800-97
Wingspan: 31’7″
Length: 30’8″
Seats: 1
Statler, William H
Bill Statler was a former Lockheed engineer who designed an all-metal midwing racer, Little Mike, in the Goodyear 190-ci. Class.
William H Statler, of Northridge CA., built the Dos Equis Challenger unlimited racer and Statler Firefly in 1982 and 1976 respectively.
Start & Flug H-101 Salto / Super Salto
The H 101 Salto is an aerobatic version of the Standard Libelle developed by Frau Ursula Hanle, widow of Ing Eugen Hanle, the former Director of Glasflugel; the Salto (this word is German for loop) is produced by Start + Flug GmbH formed by Frau Hanle.
The design of this single-seat 13 metre sailplane draws extensively on that of their glassfibre sailplane, the H-30, designed by Hutter, and of the Standard Libelle. The Salto is manufactured so that several components are interchangeable with those of the Libelle.
The Salto differs from the Standard Libelle largely in having a V-tail with an included angle of 99°. The Salte also owes something to the V-tailed Hiitter H-30 GFK. Four flush-fitting air brakes repositioned on the wing trailing edges replace the more conventionally-sited air brakes of the Standard Libelle; the Salto’s air brakes are hinged at their mid-points so that half the surface projects above the wing and half below. The fuselage has a fixed, faired wheel, and a tailskid, and the one-piece canopy is hinged to open sideways.
The Salto employs a Standard Libelle wing shortened at the root to produce a span of 13.6 m (44 ft 7.5 in), and fitted with trailing edge dive brakes and a tail parachute for approach control. Tip extensions have been designated extending the wingpspan up to a much as 15.8 m/ 51.8 ft. G limitations are +7 and -5.
The Salto prototype first flew in March 1970 and 60 had been delivered by the spring of 1977; German type certification was granted on 28 April 1972 and the Salto has also been certificated by the FAA as well as Germany in the Normal and Aerobatic catergories.
Later production was by Dokter Fiberglas.
Bob Carlton’s Super Salto has been retrofitted with a 225 lb thrust jet from PBS in the Czech Republic. Powered by this new Jet engine, the highly modified Super Salto jet sailplane self-launches and performs both a classic sailplane aerial ballet and screamin’ low-level jet aerobatics.
The first flight of the Super Salto Jet Sailplane took place on October 8, 2008.
Start + Flug Salto
Wing span: 13.6 m (44 ft 7.5 in)
Length: 5.95 m (19 ft 6.25 in)
Height: 0.88 m (2 ft 10.75 in)
Wing area: 8.58 sq.m (92.4 sq ft)
Wing section: Wortmann FX-66-17-Al 1-182
Aspect ratio: 21.6
Empty weight: 180 kg (397 lb)
Max weight: 310 kg (683 lb)
Water ballast: None
Max wing loading: 36.13 kg/sq.m (7.4 lb/sq ft)
Max speed: 135 kt (250 km/h)
Stalling speed: 35 kt (65 km/h)
Min sinking speed: 0.6 m/sec (2 ft/sec) at 40.5 kt (75 km/h)
Max rough air speed: 135 kt (250 km/h)
Best glide ratio: 35 at 48.5 kt (90 km/h)
H101 Salto Normal
Wing span: 13.6m /44.6ft
Wing area: 8.58sq.m / 92.4sq.ft
Empty Weight: 182kg / 401lb
Payload: 98kg / 216lb
Gross Weight: 280kg / 617lb
Wing Load: 32.6kg/sq.m / 6.68lb/sq.ft
Aspect ratio: 20.6
Airfoil: Wortmann
L/DMax: 34 94 kph / 51 kt / 58 mph
Min Sink: 0.70 m/s / 2.3 fps / 1.36 kt
Seats: 1
H 101 Salto Aerobatic
Wing span: 13.6m / 44.6ft
Wing area: 8.58sq.m / 92.4sq.ft
Empty Weight: 182kg / 401lb
Payload: 98kg / 216lb
Gross Weight: 280kg / 617lb
Wing Load: 32.6kg/sq.m / 6.68lb/sq.ft
L/DMax: 34 94 kph / 51 kt / 58 mph
MinSink: 0.70 m/s / 2.3 fps / 1.36 kt
Aspect ratio: 20.6
Airfoil: Wortmann
Seats: 1
Starr Bumble Bee II
This 1988 plane had a wingspan of just 1.9-meters. and was powered by an 85hp engine. Unfortunately, the plane crashed on its maiden flight but the pilot Starr made a full recovery. The plane weighed 260kg with the pilot and could fly at a maximum speed of 190mph. This record has not yet been beaten.
Engine: 1 × Continental C85, 85 hp / 63 kW
Wingspan: 5 ft 6 in / 1.68 m
Length: 8 ft 10 in / 2.7 m
Empty weight: 396 lb / 180 kg
Max takeoff weight: 574 lb / 260 kg
Fuel capacity: 3 US gallons / 11.35 litres
Maximum speed: 165 knots / 190 mph / 305 km/h
Cruise speed: 130 knots / 150 mph/ 241 km/h
Stall speed: 75 knots / 86 mph / 139 km/h
Service ceiling: 14,000 ft / 4,270 m)
Rate of climb: 4,500 ft/min / 23 m/s
Crew: One
Starr Bumble Bee
The Bumble Bee II was the world’s smallest piloted airplane. It was built by Robert H. Starr. Its first flight was on 8 May 1988. The Bumble Bee II crashed on the same day due to an engine failure. Robert Starr was seriously injured in the crash, but he fully recovered from his injuries.
Engine: 85hp Continental C-85
Wingspan: 6’6″
Length: 9’4″
Fuel capacity: 3-gal
Max speed: 180 mph
Cruise: 150 mph
Stall: 80 mph
Range: 30 mi
Ceiling: 5,000 ft
Seats: 1
Star-Lite Warp 1-A
The Star-Lite Warp 1-A is an American homebuilt aircraft that was designed and produced by Star-Lite Engineering of Englewood, Ohio, introduced in 1996.
The aircraft was designed to comply with the US FAR 103 Ultralight Vehicles rules, including the category’s maximum empty weight of 254 lb (115 kg). The aircraft has a standard empty weight of 250 lb (113 kg). The original Star-Lite used a Rotax 447 engine.
The Warp 1-A features a cantilever mid-wing, a single-seat enclosed cockpit under a bubble canopy, fixed tricycle landing gear with wheel pants, a boom-mounted T-tail and a single pod-mounted engine in pusher configuration.
The aircraft is made from composites. Its 25.0 ft (7.6 m) span wing is made with an aluminum spar and S-glass vinyl-ester resin, is detachable for ground transport or storage and has a wing area of 87.5 sq ft (8.13 m2). The standard engine used is the 50 hp (37 kW) Rotax 503 two-stroke powerplant.
Introduced in 1996, the aircraft was supplied as a kit for amateur construction. The manufacturer estimated the construction time from the supplied kit as 100 hours. The kit, including engine, propeller and instruments, cost US$26,995.00 in 1998.
In March 2014 one example, the prototype, was registered in the United States with the Federal Aviation Administration as an Experimental – Amateur-built, although its registration expired in June 2013.
Brian Burghgrave built a Star-Lite M2 using a Rotax 503, necessitating a new cowl. In addition, he installed flaps and counterbalanced the ailerons and elevator. First flown in October 2009, these changes add the “M2” to the name.
Top speed: 70 mph
Cruise: 55 mph
Stall: 22 mph
Range: 100 sm
Rate of climb: 900 fpm
Takeoff dist: 50 ft
Landing dist: 50 ft
Service ceiling: 12,000 ft
Engine: Rotax 503, 46 hp
HP range: 40-100
Fuel capacity: 5 USG
Empty weight: 250 lb
Gross weight: 575 lb
Height: 6.5 ft
Length: 19.5 ft
Wing span: 25 ft
Wing area: 87.5 sq.ft
Seats: 1
Landing gear: nosewheel
Star-Lite Warp 1-A
Engine: 1 × Rotax, 50 hp (37 kW)
Propeller: 2-bladed fixed pitch
Wingspan: 25 ft 0 in (7.62 m)
Wing area: 87.50 sq ft (8.129 sq.m)
Aspect ratio: 7:1
Empty weight: 250 lb (113 kg)
Gross weight: 575 lb (261 kg)
Fuel capacity: 5 U.S. gallons (19 L; 4.2 imp gal)
Full fuel payload: 295 lb (134 kg)
Wing loading: 6.6 lb/sq ft (32 kg/sq.m)
Cruise speed: 95 mph (153 km/h, 83 kn)
Stall speed: 40 mph (64 km/h, 35 kn)
Never exceed speed: 110 mph (180 km/h, 96 kn)
Service ceiling: 12,000 ft (3,700 m)
Rate of climb: 900 ft/min (4.6 m/s)
Take-off & landing roll: 150 ft (46 m)
Crew: one
Star-Lite Engineering
1997: 11509 Diamond Mill Rd, Englewood, OH 45322, USA.
UL builder
Star Kraft Inc
1993: Star-Kraft,
Ft Scott KS.
USA
First flew in 1994 the all-composites Star Kraft 700 eight/nine-seat pressurized business aircraft with nose and tail piston engines. Projected variants are the 700- SE with one engine and fixed undercarriage, 1100 12- seat lengthened version, and 500 five-passenger single-engined model.
All Aero 