This Data take with Vittorazi Cosmos 300 Note TrueLite long wing with slotted flap meet Far103 (The provided information needs to be updated) Stall speed with flaps: 44 km/h (24 knots) Maneuvering speed: 100 km/h (54 knots) Cruising low speed: 70 km/h (37 knots) Cruising speed: 105 km/h (55 knots) Vne : 173 km/h (94 knots) at lower cruise speed 5 liter per hour TrueLite (Zigolo Mg21) short wing stall speed half span gurney flap installed 60kmh 32knot Va maneuvering speed 100kmh 54knot Vh max speed full power 125kmh 67knot Vc cruse speed clean 105kmh 55knot Vne with gurney flap installed 140kmh 76knot Vne clean airfoil 173kmh 94knot Cg margin= from 25% to 35% from leading edge standard consumption include take off at standard cruise speed 100kmh 8.5 liter per hour

long wing with flap length 6.3m width 1.9m Height 1.6m https://static.wixstatic.com/media/693cb9_3d09cddce45740b4b91fa1b27b97097a~mv2.png

load limitation Tested 4G on load wing without deformation Design load based on CS-VlA Ltf-ul , Far 23 bcar-s limitation Max weight +4 -2 G 220kg Safety Factor 1,5 Empty weight with parachute = 114kg The structural calculation takes in consideration fatigue of material, the elastic limit of this airplane is below 4g, deformations can occur after this limit. The safety factor is 1,5g and higher according to the prescriptions of the regulations. The speed limitations give a large margin in flight because the manoeuvring speed, it goes beyond the cruising speed, under this speed the stall occur before achieving the critical load, flight ad higher speed is limited by the aerodynamic of this aircraft. Load tests show that it is a robust airplane for the type of use. This means that plastic deformations can occur after 4g, under this load we are in elastic range. But the characteristic of this aircraft are calculated to support +4g -2g on the flight manual we give you a table to understand how the VA speed change depending of total load, we have standardized manoeuvring speed at 100km/h that give good margin of different load and speed error. Load test The most problematic area in the sheet metal construction are the concentration of buckling. we have based all calculation on this particular effect, we have load 6g on the tail, and we have not see any permanent deformation. to make this test we have inverted the aircraft and we lock the tail and seat to have most realistic possible load situation. Due to weight distribution when we reached 4g on the wing, we had reached 6g on the tail. The tail support it without permanent deformation, to end the load test we moved the weight on the wing tips, with this method we have tested 6g bending moment on the wings without deformation, we have test complete load on wing and fuselage support 4g than make this aircraft ready in case of certification. during the calculations all the asymmetrical loads prescribed by the regulations were taken into account, the loads on the anchor points parachute belts this aircraft has been designed with a deep study to minimize the components and make it as simple as possible. new wing with flap is design to 220kg MTOW https://static.wixstatic.com/media/693cb9_666d395fe0f7489cad85967cbb856873~mv2.png https://static.wixstatic.com/media/693cb9_a1398004049b434787c0049e9980d101~mv2.png https://static.wixstatic.com/media/693cb9_8ae1df733b4b4a40bda4547544c2836e~mv2.png https://static.wixstatic.com/media/693cb9_b28e8dcdbcc84b7f99b554e840c3a164~mv2.png https://static.wixstatic.com/media/693cb9_21132c35839f41529e23d55355dd7d8c~mv2.png Short wing V- diagram https://static.wixstatic.com/media/693cb9_35af6b9a03064fc7b5e34db978eb9295~mv2.png

sheet metal construction 6061t6 web Spar with aluminum cup, formed rib, leading edge skin aluminum, aileron in aluminum covered with Dacron Fabric Wingspan 8,2 m Chord line 1 m Wing area 8,2 m Aspect ratio 8,5 Taper ratio 1.0 Dihedral 1.5° the wing is built completely in aluminium. https://static.wixstatic.com/media/693cb9_c9ccdf09d01e4274bcbaf2178563e824~mv2.jpg

Vertical tail and horizontal Tail surface are made with aluminum tube and sheet metal ribs, covered with pre-sewn bag The installation is simple, it slips into the surfaces and is heated with an iron, it can be painted in the color you prefer. The 2 surface are fixed with bolt, can be dismounted for transport. Rudder is connected with stainless steel wires, and elevator is connected with Teleflex cable. horizontal tail have regulation and can be adjusted depending aircraft configuration Gurney flap or not. https://static.wixstatic.com/media/693cb9_0f22699119b64b38bd0fdfc0a958c915~mv2.png

landing gear use differential brake each one is operated by pivoting of the rudder pedal. the main landing gear use 7075 aluminum conical bar, then support the interchangeable axle for change wheel. tail wheel is fixed with the rudder, and is made with conical bar in 7075 aluminum. Wheel Track 1,2 m Wheel Base 3.1 meter Tail wheel 120 mm Aviad wheels Front tires bicycle disk and brake caliper Tyre 4-6" 340diameter x 110 wide mm 5.3kg 2 set wheel 10" hydraulic disc brake Beringer Front tire hydraulic disc brake wheel 4"x 300mm diameter 4.7kg complete *standard weight wheel 6"x 370mm diameter 11.2kg complete https://www.beringer-aero.com/sites/beringer-aero.com/files/cata_en.pdf (https://www.beringer-aero.com/sites/beringer-aero.com/files/cata_en.pdf) old pictures now is anodized and machined with new profile https://static.wixstatic.com/media/693cb9_a341f6c10dcc4ba585d6a88d0d516836~mv2.jpg https://static.wixstatic.com/media/693cb9_bc3f2f0e074141c0b6fc98ea160c4e4b~mv2.jpg https://static.wixstatic.com/media/693cb9_8e1a26b2126641db9ee620bf8d62463c~mv2.png

Overall Length 4,3 m Overall Width 0.5 m Overall Height 1,6 m https://static.wixstatic.com/media/693cb9_fe28fd8fbcab470db56f49ab25d3e40c~mv2.jpg

VITTORAZI cosmos 300 Factory Vittorazi Motors https://static.wixstatic.com/media/693cb9_a74ce29c1f2b4a1787f3fbe5c6212927~mv2.png https://static.wixstatic.com/media/693cb9_1b682fc0ac7741a38924892f803e3190~mv2.jpg

Gasoline grade 95 octane mixed with oil to 2.5% Synthetic Oil Motul 710 2%, 1:50 Synthetic Oil Motul 800 1.5%, 1:66 make reference manual engine Vittorazi cosmos 300

Fuel tank Standard in robust plastic tank fixed on fuselage. Total capacity of 18 Liters * Standard wing tank additional wing tanks, can be installed inside the wings, the tanks are made with aluminum tubes of the same diameter as the lightening of the ribs. Each tank can store 5.8 liters x 4 23liter *optional

Parachute Model Cylindrcone – automatic emission Safety belt 4 point https://static.wixstatic.com/media/693cb9_bddb6a6f909041d290753fb258c79b62~mv2.jpg

You will choose the color of the plane !! this aircraft is mainly built in sheet metal, to save weight a Dacron canvas covering was opted for tails flap and aileron. This type of canvas allows you to paint the canvas in the color you want, by spray or by hand. Oratex prepaint fabric is also available the finish and tension of this type of material is done with an iron, the result is a perfectly taut finish without any kind of wrinkle. The advantage of this airplane, tail surface and aileron are supplied with a pre cut tailor-made , it will be enough to insert the fabric into the surfaces, add glue with brush and heat the surface, the result is a taut surface like that of a drum. The wings are completely in aluminium. the durability of this canvas is very high 15 years but many aircraft use this for more year, it resists well to sun exposure, and is easy to repair, all repairs can be carried out with gluing and therefore the problem of having resistant seams is eliminated. https://static.wixstatic.com/media/693cb9_4352d59a6eb84a1592046dc3d33a839b~mv2.jpeg https://static.wixstatic.com/media/693cb9_c8ddfe694a6b49908d427053677a3809~mv2.png https://static.wixstatic.com/media/693cb9_17306ad301874b6e8ef5d12994d80e24~mv2.png https://static.wixstatic.com/media/693cb9_f9c52abbad9f41d89b568664d27c7275~mv2.png

Il TrueLite è conforme a FAR103 SSDR DGAC Il Zigolo MG21 (ala corta) ha subito significative modifiche. È stato rinominato e ora viene prodotto come TrueLite. L'originale Zigolo MG21 senza flap Gurney non soddisfaceva lo standard Part 103. Con la transizione a TrueLite, sono state apportate alcune modifiche all'aereo: È stato aggiunto più spazio per le gambe per il comfort del pilota. L'apertura alare è stata aumentata per soddisfare il FAR 103. Sono stati integrati flap slotted per garantire che l'aereo soddisfi i requisiti del FAR 103. Dettagli specifici sul TrueLite includono: Un peso a vuoto d: il Zigolo MG21 pesava 100kg (220lb) senza un paracadute da 7kg e con riserva di benzina. adesso abbiamo un peso a vuoto di 114kg senza paracadute.