A tandem two-seat composites, built developed from single-seat Piel CP.150 Onyx and featuring rear-mounted wings and high canard. The fuselage is in wood and composites with the kit including all mouldings. The engine is limited to 55 kg for CoG reasons.
Onyx bi 582 Engine: Rotax 582 DCDI, 64 hp Wing span: 9.20 m Wing area: 16.07 sq.m MAUW: 440 kg Empty weight: 220 kg Fuel capacity: 50 lt Max speed: 185 kph Cruise speed: 150 kph Minimum speed: 64 kph Climb rate: 5 m/s Seats: 2 Fuel consumption: 13 lt/hr Kit price (1998): 117 800 Fttc
Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading edge, swept for¬ward trailing edge and tapering chord; cruci¬form tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by one third span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile; double surface. Undercarriage has three wheels in tricycle formation with additional tailskid; steel spring suspension on all main wheels. Push right go right nose¬wheel steering connected to yaw control. Brakes on main wheels. Aluminium tube framework, without pod. Engine mounted above wing driving tractor propeller. Cover¬ing is transparent Mylar; push pull tubes for flight controls.
The prototype of this single seater appeared at the end of 1982 and presented at the March 1983 Sun In’ Fun in Lakeland, Florida, where it enjoyed a certain success. It is certainly one of the better conventional three axis designs on the American market; for instance, the controls are operated by push rods and the wing is supported on struts rather than cables, features which allow one to rig the aircraft in around 20 min. The wings fold parallel to the fuselage allowing easy transport on a trailer without any other derigging.
The Meadowlark was fitted with a Cuyuna 430R engine with Arizona Air Sports reduc¬tion drive and was sold only in ready to fly form, at a price of $6575. Biam floats were available as an option for $975; other options include flight and engine instruments.
Engine: Cuyuna 430R, 30 hp at 5500 rpm Propeller diameter and pitch 54 x 27 inch, 1.37 x 0.68 m V belt reduction, ratio 2.0/1 Max static thrust 197 lb, 90 kg Power per unit area 0.22 hp/sq.ft, 2.4 hp/sq.m Fuel capacity 3.7 US gal, 3.1 Imp gal, 14.0 litre Length overall 19.0 ft, 5.79 m Height overall 7.3ft, 2.21m Wing span 35.0ft, 10.66m Chord at root 5.0ft, 1.52m Chord at tip 3.0ft, 0.91m Dihedral 3 deg Sweepback 0 deg Tailplane span 8.6 ft, 2.59 m Fin height 3.4 ft, 1.01 m Total wing area 136 sq.ft, 12.6 sq.m Total aileron area 12.0 sq.ft, 1.11 sq.m Fin area 7.5 sq.ft, 0.69 sq.m Rudder area 5.0 sq.ft, 0.46 sq.m Tail¬plane area 14.0 sq.ft, 1.30 sq.m Total elevator area 7.0 sq.ft, 0.65 sq.m Wing aspect ratio 9.0/1 Wheel track 5.0ft, 1.52 m Wheelbase 5.0ft, 1.52 m Nosewheel diameter overall 19 inch, 48 cm Main wheels diameter overall 23 inch, 58 cm Optional floats: 11.0 x 23.5ft, 3.35 x 7.13 m Empty weight 251 lb, 114 kg Max take off weight 550 lb, 249kg Payload 299 lb, 136kg Max wing loading 4.04 lb/sq.ft, 19.7kg/sq.m Max power loading 18.3 lb/hp, 8.3kg/hp Load factors +3.8, 1.5 design Max level speed 55mph, 88kph Never exceed speed 60mph, 97kph Max cruising speed 55mph, 88kph Economic cruising speed 35mph, 56kph Stalling speed 22 mph, 35 kph Max climb rate at sea level 1000 ft/min, 5.1 m/s Min sink rate 400 ft/min at 27 mph, 2.0 m/s at 43 kph Best glide ratio with power off 8/1 at 30 mph, 48 kph Take off distance 75 ft, 23 m Landing distance 100ft, 30m Range at average cruising speed 90 mile, 145 km
The Model 100 Adventure’s simplicity of operation is equaled only by its simplicity in construction. A modern, high performance, sandwich composite structure was used throughout. The materials and working techniques are descendants of Rutans VariEze technology. The Adventure has a combination of high speed cruise, low stall speeds and good climb performance.
The general configuration is a single-seat, low mid-wing tractor monoplane with fixed tricycle landing gear that may be powered by any of the Con¬tinental Motors A or C series engines of 65 to 85 hp driving a fixed-pitch wooden propeller. The wing is a two-piece assembly to minimize the space required to build and to facilitate its removal from the fuselage. The fuselage is built from flat sheets of half-inch-thick polystyrene foam and constructed from the inside out. The canopy is a single-piece, free-blown unit.
Aileron rolls and one turn spins are the only aerobatics that the Adventure has performed. It is intended to be a utility category aircraft with lots of structural beef and a conservative repertoire of aerobatic maneuvers.
Engine 65 to 100-hp Continen¬tal Gross Wt. 800 lb Empty Wt. 460 lb Fuel capacity 20 USG Wingspan 20’ Length 13’ Wing area: 40 sq.ft Top speed 188 mph Cruise 180 mph Stall mph 57 Climb rate 1600 fpm Takeoff run 800 ft Landing roll 700 ft Range 650 miles Seats: 1.
The “Rhon Ranger” is a type of primary glider (or Zogling variant), designed in Europe, for which plans were published in America in the 1930s. In America it is called the “Mead” primary glider after the Chicago firm that marketed Rhon Ranger kits and plans there.
The glider consists of a simple open wooden frame fuselage with doped fabric covered section at rear, fabric covered wooden framed wing of constant cord, fabric covered wooden framed tailplane, elevators and rudder.
The airframe, when assembled, is braced with tubular metal struts. In addition the wing root joint between the wings is covered by plywood panel fairings.
A Rhon Ranger was built by Mr Renaut of South Shiels, UK, in 1932, as the Renaut Primary. It was first flown at Simonside in July 1932.
The two-seater MDM-1 FOX glider has been developed on base of design experience acquired during work with KOBUZ, JANTAR and SWIFT S-1 gliders by the team of Edward Marganski M.Sc. (Eng.). Designed by E.Marganski, K. Kapinos, H. Gielbaza, and B Adamski, work started in November 1992 and the first prototype was flown on 9th July 1993.
Marganski MDM-1 Fox G-IIFX
Capable of arotowing and winch-launching, the Fox is optimized for aerobatic training with erect and inverted clearance to +9/- 6 g solo, and +7/-5 g with two people. The landing gear is fixed, and approach control is assisted by Schempp-Hirth airbrakes.
Almost immediately after the 1-st presentation at World Glider Aerobatic Championships, Venlo Netherlands 1993 the Fox model has gained a status of monotype at every serious international championships in glider aerobatic.
Certification is EASA TYPE CERTIFICATE No A.039.
The MDM-1 Fox P is a version with redesigned exchangeable wing tips. Depending on the mounted wing tip, the glider can be used in one of two versions:
Aerobatic – without wing-tips, wing span of 14,00 m.
Utility – with wing-tips extending wing span to 16,15 m. Glider in this version can perform only basic aerobatic manoeuvres. Wing-tips with elliptical sweep and dihedral lift based on an arc.
The base price in 2011: 91 850 € TTC EXW (76 800 € HT EXW) As at November 2013 the prices were: MDM-1 Fox glider in basic version: 75 000,00 € MDM-1P Fox glider in aerobatic / utility version: 76 500,00 €
MDM-1 Fox Wing span: 14 m / 45.9 ft Wing area: 12.34 sq.m / 132.8 sq.ft Length: 7,38 m Height: 2,25 m Empty Weight: 345kg / 761lb Payload: 180kg / 396 lb Aspect ratio: 15.88 Gross Weight: 525 kg / 1157 lb Wing Load: 42.54 kg/sq.m / 8.71 lb/sq.ft MinSink: 0.8 m/s / 2.62 fps / 1.55 kt Vne (max never exceeded speed): 285 km/h / 152kts Airfoil: NACA 64(1)412 Structure: GFRP/CFRP Max G-Force: +9 / -6 G Seats: 2
MDM-1 Fox P Aerobatic Wing span: 14,00 m / 45,9 ft Length: 7,38 m / 24,2 ft Height: 2,25 m / 7,4 ft Wings area: 12,34 sq.m / 132,8 sqft Vne(max never exceeded speed): 282 km/h / 152kts Max take-off weight: 530 kg / 1168,0 lb Max empty weight: 350 kg / 772,0 lb Max G-Force (1 person crew): +9 / -6 G Max G-Force (2 person crew): +7 / -5 G
MDM-1 Fox P Utility Wing span: 16,15 m / 53,0 ft Length: 7,38 m / 24,2 ft Height: 2,25 m / 7,4 ft Wings area: 13,09 sq.m / 141,0 sqft Vne(max never exceeded speed): 282 km/h / 152kts Max take-off weight: 535 kg / 1179,0 lb Max empty weight: 355,0 kg / 783,0 lb Max G-Force (1 person crew): +5,3 / -2,65 G Max G-Force (2 person crew): +5,3 / -2,65 G
The EM-11 was designed by Edward Margański of Margański & Mysłowski Zakłady Lotnicze (Margański & Mysłowski Aviation Works). Work on this low cost, light utility aircraft, of unorthodox configuration, with slim glider-like fuselage and two pusher engines, started in 2001. The plane was constructed of composite materials with a car-like 4-seat cabin placed low to the ground. Room for cargo was created aft of the rear seats.
A four seater twin-engine aircraft with retractable landing gear, high-wing configuration, the shell structure is all-composite with honeycomb filler. Wings have foldable tips for easier hangaring. Two fuel tanks of 200 litres capacity each are installed in wings. Fuselage has upwards-opening door in the front part and cargo hatch in the central part. Passenger cabin has four separate seats, of which the front ones are reclining and sliding. The seats have 3-point inertial safety belts. Tail plane is in T type. Electrical trimming tabs are mounted on both planes. Flight control systems are controlled by a rigid push-rod transmission system, the rudder is controlled with use of a line. The aircraft is propelled by two counter-rotating engines LYCOMING IO-320 / LIO-320 of 160 hp each at 2,700 RPM. 3-blade constant-speed type MT-Propeller propellers are fitted. Hydraulically retracted landing gear is mounted on fuselage and has gas shock absorbers with hydraulic damping.
The first prototype EM-11, registered SP-YEN, first flew on August 8, 2003. It has a fixed tricycle landing gear and Rotax 912 (100 hp) engines. The second prototype, registered SP-YEP, being a pattern for serial production variant EM-11C, flew 20 October 2005 with Lycoming IO-320 engines and retractable landing gear. In April 2011 EM-11C Orka was EASA certified and in production. Prior to certification, the prototypes and three further aircraft had been built.
EM-11C Orka (SP-YEP)
Several variants were planned including, a patrol aircraft with an FLIR head, an air ambulance, a cargo plane, and an amphibious version.
An aerobatic trainer / tourer, the prototype first flying in 1983. MDB Flugtechnik AG was founded 1991 to continue development of the MD3-160, as begun by MDC Max Datwyler AG, which was being manufactured in Malaysia by SME Aviation as the MD3-160 AeroTiga. The first Malaysian-built example in flew 1995.
All Aero 