A 1956, single place, two co-axial rotor helicopter. Power was a 70hp McCulloch engine.
Author: Terry
Nagler NH-120
This 1954 ultra-light single-seater has two rotors: one main rotor with collective and cyclic pitch control, the latter by a hanging stick, and one smaller anti-torque rotor. Nagler’s ingenuity in this design consists in placing the latter above the main rotor, which is thus surmounted by the driving engine directly above it and a two-bladed, much smaller diameter fixed-pitch rotor. This compact unit, two rotors with the engine between them, is supported by the helicopter frame made of tubes and containing the pilot’s seat with fuel tanks behind it. The 45hp engine originally planned for proved insufficiently powerful and has been replaced. The tricycle landing gear has three wheels held at the end of legs fitted with shock absorbers.
When folded this rotorcraft will go into a container measuring 0.77 by 2.13m.
NH 120
Engine: Nelson, 40hp
Upper rotor diameter: 2.13m
Lower rotor diameter: 6.1m
Length: 8 ft 2 in
Height: 2.74m
Weight empty: 127kg
Weight fully loaded: 340kg
Max speed: 80 mph
Cruising speed: 112km/h
Range: 210 mi
Endurance: 3h
Crew: 1
Nagler Convertocrapt 130
This 1954 convertiplane consisted of an Aeronca fuselage minus the wings and plus a two-bladed rotor powered by six solid fuel rockets placed three at the tip of each blade and each providing a 41-68kg thrust.
The airscrew used for forward flight was powered by a Continental reciprocating engine.
After the rocket power take-off, the Convertocraft flies forward with the rotor freewheeling.
Engine: Continental, and 6 rockets
Rotor diameter: 30 ft (9.14 m)
Weight fully loaded: 1,450 lb (658 kg)
Cruising speed: 80 m.p.h. (128 k.p.h.)
Number of seats: 2
Nagler XNH-I Heliglider / XNH-2 Heligyro
This, the first rotorcraft (1952) which Nagler designed after his arrival in the United States, was of the ‘strap-on’ variety. Its intended use was to cross rivers or other obstacles. The required height was to be reached by power from six solid-propellant rockets, fired in pairs and providing a 9kg thrust for about twenty seconds. Slow descent was ensured by the auto-rotation of the rotor. The six rockets could be replaced for later use.
The wearer’s legs were to be the landing gear.
With the addition of a 2 cylinder opposed engine driving a pusher prop also in 1952, the XNH-1 was re-designated XNH-2 Heligyro.
XNH-I Heliglider
Engine: 6 x 9 kg rockets
Weight empty: 29.5kg / 67 b
Crew: 1
XNH-2 Heligyro
Max speed: 60 mph
Crew: 1
Nagler Helicopter Company Inc.
Bruno Nagler, whose earliest rotary wing experiments go back to 1929, emigrated to the United States in 1952.
There he has built various prototypes, all single-seat, like his former designs, but with a totally different concept of an anti-torque rotor in the extension of the main rotor.
Nagler’s Model NH-160 single-seat helicopter first flew in 1955. The VG-1 Vertigyro developed later comprised a Piper Colt aircraft fuselage with conventional engine. Its rotor system was driven by a turbine engine, enabling the craft to be flown as a gyroplane, a helicopter, or a combination of both.
1938-1945: (Bruno) Nagler-Rolz Flugzeugbau
Vienna
Austria.
1950:
Nagler Helicopter Company Inc
White Plains NY
1971
Nagler Aircraft Corp
Phoenix AZ
1974
Phoenix Heligyro Corp.
NA Design NA-40 Bongo
Design work of the (formerly Unis, Obchodni Spol, Sro) Bongo began in 1992 followed by model tests in 1993 with construction of a technology demonstrator started in 1996.
A public debut was at Ârno International Machinery Fair 1997 (then called TINTS NA40 and with two-blade main rotor) by the first prototype, OK-CIU. The prototype began 70 hours of tethered hover flights in March 1998, and two further prototypes were completed by mid-1998.
NA Design planed Normal category certification to FAR Pts 27, 33, 34 and 36 by late 2003, subject to finding joint venture Western partner to share certification, manufacturing and marketing costs. In 2002 financial support of US$2.5 million was still being solicited. The project was put on hold in late 2002 while finance was sought but, despite this, a new version, the four-seat NA50, was announced in late 2002.
Nothing further had been heard by early 2003.
The NA Design NA 40 Bongo two-seat ultralight helicopter features a three-blade teetering rotor and pod and boom fuselage with an inverted Y-tail unit. A Cocomo patented anti-torque system eliminates the need for a tail rotor, reducing transmission complexity and operating noise level.
Flying controls were conventional cyclic and collective, with a ducted air anti-torque system. The structure is mainly composites, including the rotor blades. Some aluminium is in the fuselage, otherwise it is a double-curvature monocoque sandwich, with a laminated, vacuum-formed elastomeric rotor head. The landing gear is a tubular twin-skid gear with ground handling wheels. Inflatable permanent or emergency floats are optional.
Power is from two 86kW Prvni Brnenska Strojina PBS Velka Bites ÒÅ 50Â turboshafts, with FADEC and dual ignition. The engines are mounted side by side behind the cockpit with transmission via a combining gearbox. A single self-sealing fuel tank is beneath the engines, with a capacity of 210 litres.
A baggage space is aft of the two seats and gull-wing window/doors are on each side, hinged on the centreline and opening upward. A dual 27V DC electrical systems and external power receptacle are provided.
NA40 Bongo
Rotor diameter: 7.48m
Fuselage length: 6.15m
Height to top of rotor head: 2.35m
Empty weight, equipped: 480kg
Max load on external sling: 250kg
Max take-off weight: 950kg
Never-exceed speed: 280km/h
Max cruising speed: 250km/h
Econ cruising speed: 230km/h
Hovering ceiling IGE: 4,000m
Max range: 500km
NA Design
NA Design was created in third quarter of 1999, in co-operation with Moravan Aeroplanes Inc.
LSA helicopter builder
Mylius MY-104
Mylius Flugzeugwerk Gmbh & Co Kg marketed the single-seat MY-102 aerobatic and towing aircraft, two-seat MY-103 in Standard and Basic Trainer variants, and four-seat MY-104 for touring, IFR training and other uses. All are low-wing monoplanes based on a common modular design, with interchangeable sub-structures.
Mylius MY-103
Mylius Flugzeugwerk Gmbh & Co Kg marketed the single-seat MY-102 aerobatic and towing aircraft, two-seat MY-103 in Standard and Basic Trainer variants, and four-seat MY-104 for touring, IFR training and other uses. All are low-wing monoplanes based on a common modular design, with interchangeable sub-structures.
Mylius MY-102
Mylius Flugzeugwerk Gmbh & Co Kg marketed the single-seat MY-102 aerobatic and towing aircraft, two-seat MY-103 in Standard and Basic Trainer variants, and four-seat MY-104 for touring, IFR training and other uses. All are low-wing monoplanes based on a common modular design, with interchangeable sub-structures.
