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  1. Ia 26 D-600 Conventional fighter (designed by Emile Dewoitine) with optional power plant, ROLLS ROYCE MERLIN III of 1030 HP (England denies the delivery of a series requested by the FMA) or DAIMLER BENZ DB 601-A of twelve inverted cylinders of 1,100 HP (to be supplied by Spain). The Project is canceled by the B-700 (I.A.27) PULQUI I. Characteristics: wingspan 10,20 m; 8.90 m long; Wing surface 15,92 m²; Empty weight 2090 kg; Total weight 2740 kg; Maximum speed 560 Km / h; Theoretical ceiling 10000 m; Reach 1400 km; Planned weapon HS-404 20 mm, four machine guns 7.50 mm M-39 (MAC - model 1934). And here come the what if part If argentina would have carry on with the project they would had used the R-1800 models that were bought fo the I.Ae 24 Calquin Short Story: By 1942 it became clear that Hawk 75O is outdated, and the Argentine Army in urgent need of replacement. Guide aircraft factory FMA were encouraged to develop domestic fighter, the characteristics of which must exceed the machine Curtiss company performance. Fast enough engineering aircraft factory FMA Office had presented a draft of a compact single classic fighter Pacuna I.Ae.26 [2] . The plane had to have solid wood semi-monocoque construction with working plywood sheathing (fabric covering used in the handlebars height and direction), retractable main landing gear, and a fully lockable lantern cockpit. The power plant should be of 14-cylinder two-row radial engine cooling air Pratt & Whitney R-1830-G Twin Wasp, develops power 1050 hp These motors were produced in Argentina under the license and intended for installation in the developed parallel light bomber Calquín I.Ae.24 [3] . During the work on the aircraft factory I.Ae.26 Pacuna FMA has made more rapid progress compared to its peers I.Ae.24 Calquín, and on September 1, "air gun" first took to the sky. During the flight test revealed a number of drawbacks, such as poor directional stability, shields the main landing gear structure, which in a certain range of speeds began to vibrate. By April 1945 - after the production of two prototypes - the problems have been resolved. Despite the fact that the "air gun" had already expired, the command of the Argentine Air Force ordered 50 aircraft to replace the fleet of ancient fighter Curtiss Hawk 75O. Small arms serial fighters I.Ae.26 Pacuna consisted of consoles installed in four wing 12.7mm guns Browning, the aircraft could also carry two cartridges with small caliber bombs or two 250-pound (113 kg) bomb. Powerplant machines serial changed: instead of 1050 powerful engines R-1830-G installed on airplanes more powerful 1200 strong R-1830-33. I.Ae.26 Pacuna was not the fastest airplane, but was stable in flight, easy to control and forgiving pilot blunders. Also, the "air-gun" was enough maneuverability at low altitudes have greater range and, more importantly, it was easy to maintain. These qualities have led to what is on I.Ae.26 Pacuna command of the Argentine Air Force fighter escorts were assigned the task light bombers I.Ae.24 Calquín, as well as lung function stormtroopers. Clean fighters originally purchased in began in Italy in 1947, thirty G.55A FIAT [4] . A year later, the Italian machines were supplemented by a first modification of the British fighter jet Gloster Meteor. Combat employment of fighter I.Ae.26 Pacuna came down to participate in the attempt of rebellion against winning the election in 1951 of President Juan Domingo Peron and during overthrew his "Liberation Revolution" in 1955 . If in 1951 the participation of "blowguns" was episodic (the machine is not even raised in the air), then in 1955 they fired at positions of Peronists and dropping bombs on them. On fighter-attack aircraft armed with light I.Ae.26 Pacuna before the start of the sixties, after which they, like other piston aircraft were replaced by jet machines American and British production - North American F-86 and the last modification Sabre Gloster Meteor. Type: I.Ae.26 Pacuna Purpose: escort fighter / light attack Crew: 1 person. Powerplant: 14-cylinder two-row radial air-cooled engine Pratt & Whitney R-1830-33 Twin Waspdevelops power 1200 hp and rotating a three-bladed variable pitch propeller Dimensions: wingspan of 9.68 m length of 8.53 m height, 3.81 m wing area 17.5 m² The weight: empty 2437 kg with a full load was 3492 kg wing loading 199.5 kg / m² specific load on the power of 2.91 kg / hp. Flight characteristics: maximum speed at a height of 4700 meters 546 km / h range 1500 km service ceiling of 10,500 meters climb of 15.9 m / s Armament: four 12.7 mm Browning gun 500 pounds (227 kg) bombs IA 28 D-710 With this denomination there are plans of a passenger transport and a sketch of a light bombardment aircraft (with ROLLS ROYCE MERLIN III engines) very similar to I.A. 24 CALQUÍN, that's why it was called SUPER CALQUÍN. A mockup 1: 1 wood scale was built. Characteristics of the passenger transport version: wingspan 22.53 m; 17.50 m long; Height 5.30 m; Surface area 66 m²; Empty weight 7800 kg; 12200 kg total weight; Top speed at sea level 375 Km / h; Maximum speed at 4700 m 465 Km / h; Maximum cruising speed 430 Km / h; Maximum range 3000 Km; Climbed 5000 m in 15 min; Theoretical ceiling 8900 m; MERCURY 2x 950 hp engines, optional GNOME RHONE 2x 1050 hp. IA 29 D-720 This project is suspended in front of the arrival in 1948 of Ing. Kurt W. Characteristics: wingspan 9.50 m; 9.20 m long; High 3.40 m; 18,70 m²; Stabilizer surface 5.98 m²; Wing load 179 Kg / m²; Gauge 2.55 m; Engine ROLLS ROYCE R.B.37 (static thrust 1700 kg); Maximum speed 800 km / h; Cruising speed 630 km / h; Landing speed 170 km / h; Ascending speed 1600 m / min; Take-off run 660 m; Operating ceiling 14000 m; Absolute ceiling 15600 m; Autonomy 1,30 h; 900 km; 2250 kg; Payload 1200 kg; Maximum weight 3150 kg; 1000 l fuel (970 kg); Weaponry 150 Kg. IA 27a Like the IA 27 with a roll royce nene 2 engine I.Ae 30 B Pallavicino 01 Jet modification of the I.Ae-30 Namcu also desing by Pallavicio was to be a heavy fighter, in a class of the Gloster Meteor: one seat, 2 Roll-Royce Dewent engines each producing 3.500 of static thrust. Was desing to have 4 Hispano Suiza cannons.None built Also design to carry a vertebral gun pod of 2 20 mm canon to have a total of 6 cannons Here are its specifications: Wing span: 15,00m Length: 13,98 m Height: 4,383 m Wing area: 35,3 m2 Empty weight: 4.225 kg All-up weight: 7.950 kg Wing loading: 225 kg/sq.m Max. speed @ SL: 910 kph Max. speed @ 9150 m: 970 kph Climbing speed @ SL: 26 mps Climb speed to 9150 m: 8'22" Ceiling: 15.240m 3 tons of fuel IA Pallavicino 02 Light Bomber with 2 crew: pilo and the navigator, seated in a glazed nose or behind the pilot (with a solid nose variant) Armed with 4 Hispano Suiza cannon and 2 bombs of 900 or 1000kg each in an internal bom bay. It clould also carry 20, 75mm air to ground rockets. None built Specifications: Wing span: 18,70 m Length: 14,00m Height: 4,65 m Wing area: 46,65 sq.m Wing loading: 280 kg/sq.m Empty weight: 6.500 kg All-up weight: 13.070 kg Max. speed @ SL: 810 kph Max. speed @ 9150 m: 870 kph Climbing speed: 15,2 mps Climb time to: 9150 m in 15'55" Ceiling: 12.200 m Range with 4 t of fuel and 2 t of bombs: 3.300 km IA 37 Technical Description: The plane was fast and had a very attractive look, and the test pilots said the plane handle quite nicely. (Were planned for the third stage): profile of the symmetrical wing 10% of thickness; Elongation 2.08; Base rope 10 m; Dihedral 0 °; Incidence 0 °; Arrow 63.5 °; Duralumin structure; Static and aerodynamically compensated duralumin elevations; Surface elevones 2,4 m²; Surface area 48 m². Duralumin semimonchotic drift surface 3.3 m²; Steering rudder 1.1 m²; Arrow 72 °. Ventral landing gear (one wheel) and one at each wing end; Oil pneumatic cushioning; Hydraulic retraction; Dunlop brakes Short History: IA.37 Ala Delta - experimental aircraft developed by the Argentine FMA. The aircraft was developed under the leadership of the German designer Reimar Horten. Some sources erroneously carries the IA.37 Pulqui III. The aircraft was designed as a supersonic interceptor with a delta wing. Initially, only the airframe was built. The first flight of the glider took place October 19, 1954. airframe towed two transport aircraft Junkers Ju-52 / 3M. Flying the aircraft revealed shortcomings and are eliminated until 1958. By this time it was decided to establish a plane turbojet Rolls-Royce Derwent 5 thrust 1832 kgf. Fuel is placed in two 850-liter tanks within the fuselage. 9this is the information that idk if it is real because other source say that the project was abandon in 160)The first airplane flight took place in early 1961, as expected Dr. Horten. However, the aircraft could not reach the design characteristics and showed the maximum speed - 902 km / h. To solve this problem, it was planned to equip IA.37 turbojet engines Rolls-Royce Avon (considered options with Avon RA.3 2948 kgf thrust and thrust Avon RA.7 3401 kgf). However, the aircraft accident led to the cessation of further work on the aircraft. Four stages of study were planned: 1. Analyze behavior with a 1:10 catapultable scale model built in plywood with a weight of 5 kg; Parameters to be measured: trajectory, stability, alar profile, center of gravity; The launches were made with elastic tensors sandows in Lake San Roque; The trajectory of the model was photographed with cameras of high speed (4000 frames per second and with films of high resolution); A 1: 5 scale model with a weight of 22 kg was also used; For the Supersonic Tunnel were constructed models of 1:25 scale stainless steel. 2. Evaluate an Esc.1: 1 glider with prone position (ventral) to study the negative G accelerations (it was sustained during those years that in rough maneuvers the pilot in that position absorbed the effects more comfortably). 3. Build metallic prototype with power plant ROLLS ROYCE DERWENT V of 1632 kg of thrust to 14000 r.p.m .; Fuel in three tanks, two wings and one internal ventral, with capacity of 1700 l for 2 h of autonomy; This version had to carry ejectible seat and ventral landing gear of a wheel. 4. Replace turbines with two ROLLS ROYCE AVON R.A. 3 of 2948 kg of thrust to achieve a speed of 1300 km / h. But the last one was never achieved only one drawing First Model: Second Model: Configuration: training aircraft / interceptor Production Status First flight: random year [source number; page number] Introduction year: Status: Prototype, cancelled because of the lack of funds Number built: <if prototype, why was it cancelled?> Crew Data Number of crew: 1 Roles of crew: pilot Engine Data (Jet Aircraft) Manufacturer: Roll Royce Name: Dewert V Number of engines: 1 Injection: Centrifugal flow with compressor and turbine of single stage Fuel: Dry weight: Fuel Data Fuel tanks: 2 tank of 850 l in each wing ( a grand total of 1700 l) Fuel consumption: Power Data WEP: - Take Off Power: - Maximum Power: 1632 Kg (16 Kn) Cruising Power: - Basic Geometric Data Length: 11m Wing span: 10m Wing area: 48 m2 Height: 3.60m Flap area: Elevator area: 3.3 m2 Rudder area: 1.1 m2 Aileron area: 2.4 m2 Weight Data Empty weight: 2,300 kg Loaded weight: 4,500 kg General Performance Data (expected) Maximum speed: 800km/h Minimum speed: Landing speed: 110 km/h Cruising speed: 750 km/h Service ceiling: 11,000m Range: 2,000 km Max Speed Chart 8000 m -> 800 km/h Rate of Climb 17 m/seg 0km Hornets Model for the Pulqui 2 Just a model but a really good looking model. IA 40/43 Draft I.A. 43 was the last step of the failed development of fighter jets initiated by the Air Force Institute after the end of World War II. Conceived by Kurt Tank, the model would have been designed by designers Wilheim Bansemir and Ludwig Mitterhuber in the design offices of IAME from 1954. According to the limited information available, this single-seater supersonic fighter had wings and rudder designed according to the concepts of the area rule. To ensure its ability to overcome the sound barrier in straight and level flight, the model would have to be driven by two Bristol Orpheus 12 jet engines of 3,705 kg of thrust, which Bristol projected to develop by increasing the power of subsonic versions that, from 1955, equipped the Folland Gnat, the Fiat G.91 and the Dassault Etendard VI. Everything indicates that the preliminary design, composed of conceptual sketches, plans and models, would have reached a certain degree of development until the first half of 1955. However, the Liberating Revolution (which in September of that year ousted President Juan D. Peron) Put the project to an early end. Their German managers, too politically related to the deposed regime, had to leave the country accused of having entered Argentina with passports and false identities; Although the background of the I.A. 43 would have been filed in Cordoba. Nevertheless, the project remained alive as Tank and Mitterhuber departed with copies of the documentation for India in February 1956. The nascent Asian power welcomed the Tank project as it fit perfectly with its decision to develop A multipurpose fighter jet that allowed it to become independent of its traditional sources of supply. Between 1956 and 1967, Tank and 14 to 17 other German engineers worked with a thousand Indian engineers and technicians on the development and construction of the HF-24 "Marut" ("Spirit of the Tempest"), a clearly apparent evolution of I.A. 43. The project started in August 1956 and its initial prototype flew for the first time on June 17, 1961. Propelled by an Orpheus 703 of 2,200 kg of thrust (without post-burner), the model was built in series from 1963 and began to be operationally employed by the Air Force of that nation in April 1967. In total, 145 Maruts were built, 130 of which equipped three combat squadrons until the mid-1990s; Participating actively in the brief Indian-Pakistani conflict of December 1971. Dimensions: Wingspan, 9.00 m; Length, 15.87 m; Height, 3.60 m; Surface area, 28.00 m2. Weight: Not determined Performances: Not determined Power plant: 2 x Bristol Orpheus 12 x 3,090 kg (dry) or 3,705 kg (with afterburning). Avionics: Not determined Mission Team: Not Determined Armaments: Not Determined IA 44 Draft I.A. 43 originated in 1953 with the purpose of satisfying the Air Force's need to replace its advanced trainers I.Ae.22 DL and Prentice T.1. Drawing on the experience of the "DL" project, the design would apply its construction methods to a much more modern aerodynamic design that revealed its origins in the studies of the German Focke-Wulf. The project, proposed and conducted by Kurt Tank, was publicly announced by President Juan Perón in September 1953 and estimated to enter service in 1958. The aircraft would be a tandem two-seater composed of a semi-monocoque fuselage built in plywood of national origin, would have a retractable tricycle landing gear and would be powered by a national IAR19CR El Indio 650 hp engine (other sources mention IAR19C Of 840 hp) with metallic tripolar propeller. The detailed design progressed rapidly and, after 60,000 man-hours of work, all of the plans had been completed and another 200,000 man-hours were budgeted to build two prototypes. But several factors would have conspired from 1954 to deprive it of impulse and support to the development work. And the departure of Tank to India and the military coup of 1955 put formal and definitive term to the project. His place was eventually occupied by the North American metallic coach Beech B45 Mentor, which was built locally under license from 1959. Although no copies of this model were ever built, the project left all the plans in the plan of the Cordovan factory and at least one model of wind tunnel in the Museum of Industry of Cordoba. IA 48 Project based on the I.A.37, two-seater tandem supersonic combat aircraft, high all-weather quota. All-metal monohull construction with new duraluminium alloys and high strength special steels; Bilargueras wings that housed the elevones (system of commands with two functions: spoiler and rudder of depth), monoderiva; Possessed ejection seats of last generation. The two power plants are housed in nacelles under the wings of laminar profile; Turbines BRISTOL ORPHEUS BO-3 of 2200 kg of thrust or ROLLS ROYCE AVON - R.A.3 of 2900 kg of thrust. It had an additional thrust of two rockets installed aft. Characteristics: height 4 m; Wingspan 7 m; Length 14 m; Surface area 50 m²; 65º wing arrow; Lifting load 340 kg / m²; Estimated maximum speed 2150 Km / h 2.1 Mach; Landing speed 175 km / h; Fuel weight 10000 kg; Maximum take-off weight 16850 kg. Weponery: 4 30mm cannons or 2 30mm cannons and 400kgs in bombs