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27-414: The Djinn was developed to function as a practical implementation of the earlier experimental Sud-Ouest Ariel rotorcraft. Atypically, the rotor was driven by compressed-air jets at the end of each blade, which had the benefit of eliminating the need for an anti-torque tail rotor. The compressed air was bled from the turbine engine, and the engine exhaust was use for directional control. On 2 January 1953,

54-502: A wing is its rear edge, where the airflow separated by the leading edge meets. Essential flight control surfaces are attached here to control the direction of the departing air flow, and exert a controlling force on the aircraft. Such control surfaces include ailerons on the wings for roll control, elevators on the tailplane controlling pitch , and the rudder on the fin controlling yaw . Elevators and ailerons may be combined as elevons on tailless aircraft . The shape of

81-476: A combined Turbomeca Arrius turbine-compressor rather than the two units of the earlier aircraft. With the space made from the power changes an extra seat was fitted. Another difference was the tail unit, the Ariel II had a single fin and rudder and used jet efflux from the turbine to provide directional control, a directional vane linked to the rudder directed the efflux. The Ariel was not put into production but

108-561: A load-bearing hook . Akin to the later Aérospatiale Alouette II helicopter, the Djinn made considerable use of pneumatic systems. According to aerospace publication Flight International , considerable weight savings had been on the rotorcraft via the use of bleed air to operate various cockpit indicators and functions, including the blind-flying instruments , fuel gauges , cabin heaters , windshield demisters , trimmers , air/sea rescue hoists and crop-spraying equipment. The rotorcraft

135-558: A record in its class. During the late 1950s, an improved version of the Djinn, tentatively designated as the Djinn III or Super Djinn , was being studied by Sud Aviation, who held the intention of pursuing further development of the type at one point. As envisioned, the modifications present upon the projected Super Djinn variant would have included the adoption of the newer Turbomeca Palouste IV engine; alongside other changes, it would have possessed both greater power and endurance than

162-479: A spherical thrust bearing, was mounted on a steel pylon by means of a ball joint and rubber shock absorbers . Unlike some of the experimental tip-jet designs of the era, a 'cold' tip-jet approach was used: that there was no combustion activity present at the exhaust nozzles installed at the ends of the rotor blades. Consequently, the nozzles produced little noise in operation, and were claimed by Sud-Ouest to be "noiseless". The all-metal rotor blades, through which

189-406: Is a French two-seat light helicopter designed and built by Sud-Ouest . The helicopter rotors were driven by compressed-air jets at the end of each blade. The S.O.1100 Ariel I was first flown in 1947, it was a light all-metal helicopter with an enclosed two-seat cabin. Power was provided by a Mathis G8 engine which drove a Turbomeca compressor. The low-pressure air output from the compressor

216-538: The Ariel, the type did rely upon the same basic concept of feeding compressed air, which was generated by an onboard pump, to the tips of the vehicle's rotor blades to drive the movement of the blades. A single seat prototype, designated SO.1220 , was constructed to function as an aerial test bed for the rotorcraft's propulsion concept. On 2 January 1953, the SO.1220, which was a simple uncovered structure with an exposed seat for

243-892: The French military, a further ten countries placed orders for the type; such as a batch of six rotorcraft which were procured by the German Army . Production of the Djinn came to an end during the mid-1960s, by which point a total of 178 Djinns had been constructed; the type had effectively been replaced by the more conventional and highly successful Aérospatiale Alouette II . Some Djinns were sold on to civil operators; in this capacity, they were often equipped for agricultural purposes, fitted with chemical tanks and spray bars. Data from The Illustrated Encyclopedia of Aircraft General characteristics Performance Related development Aircraft of comparable role, configuration, and era Sud-Ouest Ariel The Sud-Ouest Ariel

270-445: The compressed air travelled to be ejected at the blade tips, consist of a spar of tapering thickness, a honeycomb -filled trailing edge , and feature faired roots to the increase their lift coefficient. It was claimed that the blades possessed a highly homogenous structure, a highly finished surface and a constant profile, and could be easily dismantled to facilitate inspection of the main spar. The blade had no risk of icing owing to

297-465: The earlier Ariel experimental tip jet helicopter had given French aviation company Sud-Ouest a strong desire to pursue development of a practical light helicopter that would harness this technology. Out of their efforts towards this aim emerged the design of a light twin-seat rotorcraft, which was promptly designated as the SO.1221 Djinn . While this newer design did not share an identical tip jet system to

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324-432: The internal current of warm air. The Djinn used relatively standard flight controls, such as the collective pitch control (upon which the throttle was positioned) and adjustable friction trims. Apart from its method of propulsion, the Djinn was a relatively conventional helicopter, featuring a two-seat side-by-side configuration in an enclosed cabin. The cockpit is provided with an array of plexiglas panels, which provide

351-490: The knowledge gained was used in the development of the Sud-Ouest Djinn . Data from The Illustrated Encyclopedia of Aircraft General characteristics Performance Related development Aircraft of comparable role, configuration, and era [REDACTED] Media related to SNCASO SO.1120 Ariel at Wikimedia Commons Trailing edge The trailing edge of an aerodynamic surface such as

378-529: The manufacturer claimed the combination to be extremely difficult for an opposing tank to sight its adversary and to defend itself during the anticipated rapid speed of engagements. Having observed the development of the Djinn with considerable interest, the French Army encouraged the construction of a pre-production batch of 22 helicopters, which were used for evaluation purposes. The first of these pre-production aircraft flew on 23 September 1954. Three of

405-407: The occupants with a high level of all-round visibility. Directly to the rear of the cockpit was the rotorcraft's single Palouste engine. The engine lacked any electronics and had to be hand-started via a crank handle located on the starboard side of the fuselage. The Djinn possessed the ability to fly at high overload weights for around 5 sec by correctly harnessing the accumulated kinetic energy of

432-419: The original production model. The Sud-Ouest Djinn was the first tip-jet propelled rotorcraft to enter production. As such, the propulsion system involved a Turbomeca Palouste gas turbine engine that drove a pump to produce compressed air, which was in turn fed into the aircraft's hollow rotor blades to exit at their tips, causing the blades to rotate. The rotor hub assembly, which freely oscillated around

459-409: The pilot, conducted its maiden flight ; early test flights of the rotorcraft proved the viability of the propulsion system. Accordingly, it was decided to proceed with the production of five two-seat prototypes, designated as the SO.1221 ; the first of these flew on 16 December 1953. Within a few days, one of the prototypes had climbed to a recorded altitude of 4,789 m (15,712 ft) to establish

486-650: The pre-production helicopters were subsequently acquired by the United States Army , designating it as the YHO-1 , for the purpose of participating in their own series of trials; according to aviation author Stanley S. McGowen, the US Army held little interest in the type. According to author Wayne Mutza, the US Army had found the YHO-1 to be an excellent weapons platform, but had been compelled to abandon interest in

513-471: The programme by political opposition to the procurement of a rotorcraft that had non-American origins. The French Army ordered a total of 100 helicopters. The Djinn was operated by the French Army in variety of mission roles, such as liaison, observation, training purposes; when flown with a single pilot, it could be outfitted with two external litters for the casualty evacuation mission. In addition to

540-404: The proof-of-concept SO.1220 performed its maiden flight ; it was followed by the first of the SO.1221 Djinn prototypes on 16 December 1953. During the subsequence test program, one of the prototypes was recorded as having achieved a world altitude record. Having been suitably impressed by the performance of the Djinn during testing, both the French Army and the German Army chose to procure

567-483: The rotor; this 'jump' technique was successfully used to achieve certification for it to be operated to carry heavy payloads, some of which could represent up to 54% of the rotorcraft's overall gross weight. The Djinn featured a two-seat cockpit as standard, which accommodated a pilot and passenger. A range of specialised equipment could be outfitted to suit mission roles, such as stretcher carriers, spray bars, radio sets, electrical systems, additional fuel tanks, and

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594-406: The trailing edge is of prime importance in the aerodynamic function of any aerodynamic surface. A sharp trailing edge is always employed in an airfoil. George Batchelor has written about: Other sharp-edged surfaces that are attached to the trailing edges of wings or control surfaces include: Other equipment that may be attached to the trailing edges of wings include: The trailing edge is where

621-434: The type, as well as a number of other customers. Operationally, the type was used for various purposes, including liaison , aerial observation , training , and casualty evacuation . The Djinn was phased out of production during the 1960s as a consequence of the greater success of the comparably more conventional Aérospatiale Alouette II and Aérospatiale Alouette III helicopters. Positive experiences that had gained from

648-405: The upper and lower surfaces of a wing meet. The angle between the upper and lower surfaces at the trailing edge is called the trailing edge angle . If the trailing edge angle is zero it is described as a cusped trailing edge. In two-dimensional flow around a uniform wing of infinite span, the slope of the lift curve is determined primarily by the trailing edge angle . The slope is greatest if

675-429: Was ducted to each of the three rotor blades to the ends of each blade. At the tip of each blade was a combustion chamber where the air was mixed with fuel and ignited. The Ariel had a short tail boom with twin vertical tail surfaces. On 23 March 1949. an improved S.O.1110 Ariel II was flown, it was a similar configuration to the Ariel I was had revised tail surfaces. The final variant was the S.O.1120 Ariel III which had

702-405: Was equipped with an uncovered tail boom, fitted with twin fins and a rudder ; both directional control and stability were provided by the controlled deflection of exhaust gases from the engine. As a consequence of the torque-free method of rotor propulsion, the Djinn did not require the presence of an anti-torque tail rotor . A simplistic wheel-equipped twin-skid arrangement was also present; this

729-413: Was retractable by the same manually-operated crank handle used for engine start. The Djinn could also be deployed with multiple armaments. In the ground-attack role, it could be equipped with a single machine gun , which was manned from the second seat of the cockpit. For performing anti-tank warfare , the Djinn was able to carry a guided missile . When deployed in an effective manner against an adversary,

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