The R.T.1 of 1917-1918 was a redesigned R.E.8
Aircraft
Siddeley Deasy Motor Car Co. Ltd
In 1909, J. D. Siddeley resigned from Wolseley and took over the Deasy Motor Co and the company became known as Siddeley-Deasy. During World War I the company produced trucks, ambulances, and staff cars. In 1915 airframes and aero-engines started to be produced as well.
Major F.M. Green served as chief engineer at the Royal Aircraft Factory and then become a part of the Siddeley-Deasy Motor Car Company. Not limited to the production of motor vehicles, the Siddeley-Deasy brand also delved into manufacture of engines and aircraft. The company was based out of Coventry and was founded by Henry Hugh Peter Deasy. While Deasy left in 1908, J D Siddeley came aboard and changed the company name to Siddeley-Deasy. From there, the company would gradually morph into the Armstrong Whitworth Aircraft firm (known formally as the Sir W.G. Armstrong Whitworth Aircraft Co. Ltd after their 1920 merger with Armstrong Whitworth) and became responsible for a large portion of Siskin production thereafter.
In April 1919 Siddeley-Deasy was bought out by Armstrong Whitworth Development Company of Newcastle upon Tyne and in May 1919 became Armstrong Siddeley Motors Ltd a subsidiary with J. D. Siddeley as Managing Director.
Based at Coventry, Warwickshire; was concerned in production of RAF R.E.7 and R.E.8 and Airco D.H.10 during First World War. Own experimental types included R.T.1 of 1917-1918, a redesigned R.E.8; S.R.2 Siskin, developed from ideas of Major F. M. Green and precursor of famous Armstrong Whitworth line of fighters; and Sinaia twin-engined bomber, completed 1921, also associated with Armstrong Whitworth. In 1919 Armstrong Whitworth and Siddeley-Deasy combined to form in 1920 Sir W. G. Armstrong Whitworth Aircraft Ltd.
Sibnia / Chaplygin TVS-2
Another organization working on a “better” An-2 is SibNIA (Siberian Aeronautical Research Institute) in Novosibirsk, Russia. In this version, the An-2MS (An-2MC in Russian) and later usually referred to as the TVS-2MS), the radial engine was replaced by a 1,100 hp Honeywell TPE331-12UHR turbine, driving a five-bladed Hartzell propeller. The first An-2MS/TVS-2MS was first flown on September 5, 2011 and by 2015 well over fifteen examples had been delivered by SibNIA and Rusaviaprom JSC, all built, from existing An-2 airframes retaining the An-2 wings and tail feathers.
SibNIA went a step further and also developed an upgraded An-2 with an entirely new composite construction high-lift, high-aspect-ratio wing. This new wing was first tested on an An-2MS which flew as a high wing monoplane. The aircraft, designated TVS-2-DT, first flew in December 2014 and had the TPE331 engine and old style tail. It then received curved wingtips on the upper wing and a new lower wing with wingtips acting as interconnecting struts. In this guise it flew on June 10, 2015, initially also with the old tail, but this was soon replaced by a new design larger and squared vertical tail as shown in the photo.
Sibnia / Chaplygin
Russia
Siberian aeronautical research institute founded in 1940s as reserve organization in war for TsAGI. In addition to aerodynamics testing and other work has developed (with Rastr Scientific-Technical Centre) the Dzhinn two-seat lightplane and builds replicas of the Polikarpov 1-16 and 1-153 fighters of the 1930s.
Savoia-Marchetti SM.101
Flown for the first time on 20 December 1947, the SM.101 was designed as a six-seat light transport and is powered by a 235 hp Walter Bora radial engine.
Welded steel-tube construction is used with fabric covering. Fowler-type flaps are fitted to the wing and dual controls are fitted.
Engine: 235 hp Walter Bora
Wingspan: 54 ft 1 in
Wing area: 322 sq.ft
Length: 33 ft 6 in
Height: 9 ft 9.5 in
Empty weight: 2910 lb
Loaded weight: 4828 lb
Max speed: 149 mpg at SL
Cruise: 140 mph at 9020 ft
Range: 777 mi
Service ceiling: 15,750 ft
Savoia-Marchetti SM.1019
The Cessna O-1 provided the basis for the Italian development of a turboprop version. A two-seat STOL light monoplane powered by a 298kW Allison 250-B17 turboprop engine, the prototype first flew on 24 May 1969.
Savoia-Marchetti SM.1019 Article
The SM 1019 was evaluated by the Italian Army Light Aviation, which ordered 80 SM.1019E1s, under the designation AL-2. Optional armament or equipment is carried on two underwing hardpoints.
Engine: Allison 250-B15G, 317 shp
Wingspan: 10.97 m / 36 ft 0 in
Max. speed: 280 km/h / 174 mph
Savoia Marchetti SM.102
Twin-engined light transport aircraft accommodating eight passengers. The first prototype flew on 24 February 1949. Originally powered with two 500 hp Ranger SVG-770-C1B, the type was modified to take two Pratt & Whitney R-985 Wasp Junior radials and a small batch was built for the Italian Air Force.
Engines: two Pratt & Whitney R-985 Wasp Junior
Wingspan: 18 m / 59 ft 1 in
Length: 43 ft
Height: 11 ft 5 in
Empty weight: 7600 lb
Max take-off weight: 5050 kg / 11133 lb
Max. speed: 330 km/h / 205 mph at 3280 ft
Cruise: 180 mph at 11,480 ft
Time to 5000ft: 6 mon
Service ceiling: 19,700 ft
Max range: 932 mi
SIAI Marchetti SF.600TP Canguro / General Avia SF600TP Cangaru / VulcanAir SF600TP Cangaru
The prototype SF600TP Cangaru (Kangaroo) general utility transport was built by General Avia and made its first flight on 30 December 1978. Production examples entered service in an air taxi role on 8 April 1988.
SIAI Marchetti SF.600TP Canguro Article
A choice of fixed or retractable undercarriage versions was available, the engines being 450 shp (335 kW) Allison 250-B17F turboprops.
Projected military versions of the twin-turboprop SF.600TP Canguro include a swing-tail cargo transport, an electronic warfare aircraft, and a maritime surveillance variant with an undernose 360o -scan Bendix RDR-1400 search radar. Two underwing and two underfuselage hardpoints are provided.
The basic utility version can be equipped with 12 inward facing seats for paradropping, four stretchers for medevac, or Zeiss type cameras for photographic reconnaissance, and can also be used for target or glider towing.
In 1990 the PADC in the Philippines started assembling S 211s, followed by SF 260 TPWs and SF 600 Canguro in agreement with SIAI Marchetti of Italy.
The SF.600 Canguro was taken over by VulcanAir.
SF.600TP
Engines: 2 x Allison 250-B17C turboprops, 450 shp (335 kW)
Max take-off weight: 3300 kg / 7275 lb
Wingspan: 15 m / 49 ft 3 in
Length: 12.15 m / 40 ft 10 in
Height: 4.6 m / 15 ft 1 in
Max. speed: 305 km/h / 190 mph
Ceiling: 7300 m / 23950 ft
Range: 1580 km / 982 miles
SIAI Marchetti SF.250 / SF.260 / Aviamilano F.250 / Waco Meteor
The prototype for the SF.260 series, known as the F.250, flew for the first time on 15 July 1964. The version developed initially for civil production was manufactured at first under licence from Aviamilano by SIAI-Marchetti and is designated SF.260 (initials in SF.260 denoted design by Stelio Frati). Subsequently SIAI-Marchetti became the official holder of the type certificate and of all manufacturing rights of the SF.260.
SIAI Marchetti SF.250 / SF.260 Article
A cabin monoplane with a cantilever low wing, the fuselage is an all-metal semi-monocoque structure of relatively thick skins and minimal stringers. The wing has a metal single spar, Friese type ailerons and electric slotted flaps. The wing is NACA 64-212 at the root and NACA 64-210 at the tip. The empennage contains cantilevered flying surfaces, with a manually operated trim tab on the elevator. The retractable tricycle undercarriage has oleo-pneumatic shock absorbers and a steerable nose wheel.
Designed by Stelio Frati and built in Italy, it is a 4 seater low-wing aircraft powered by a 260 hp Lycoming and has been predominantly sold in military versions since first flying in 1966. The SF.260 received FAA certifica¬tion on 1 April 1966.
Production of SF.260s for military use continued into 1987 in three versions: the SF.260M basic trainer, the armed SF.260W Warrior trainer and light attack aircraft, and the SF.260TP, powered by an Allison 250-B17C turboprop in place of the Lycoming 0-540 piston engine of the earlier models. The airframe is common in each case, except for a lengthened fuselage for the turboprop version. The SF.260W and TP have up to four underwing pylons for a variety of light stores, including rocket and gun pods to a maximum of 300kg.
Replacing the earlier C model, the SF.260D is powered by a 260 hp (194 kW) Textron Lycoming O-540-E4A5 engine and has the aerodynamic and structural improvements developed for the military SF260M. The similar SF260W Warrior can also double as a tactical support/liaison aircraft with light weapons. Production continues in 1990 of the SF.260TP, of which more than 60 had been ordered powered by the 350 shp (261 kW) Allison 250-B17D turboprop.
Some 350 SF260s were built in the 14 years since the type first flew. By 1993 more than 700 civil and military SF.260s of all models had been completed, most of which were for export.
Waco Aircraft was founded in 1966 to build SF.260 (as Waco Meteor), and Socata Rallye Commodore (as Waco Minerva).
In 1990 the PADC in the Philippines started assembling S 211s, followed by SF 260 TPWs and SF 600 Canguro in agreement with SIAI Marchetti of Italy.
Aviamilano F.250
Engine: Lycoming 250 hp.
SIAI-Marchetti SF.260
Engine: Lycoming O-540-E4A5, 260 hp
TBO: 2000 hr
Fuel type: 100LL
Propeller type: CS
Landing gear type: Tri./Retr
Max ramp weight: 2430 lb
Gross weight, utility: 2430 lb
Gross weight, aerobatic: 2205 lb
Landing weight: 2430 lb
Empty weight, std: 1664 lb
Useful load, std: 766 lb
Useable fuel, std: 62 USG
Payload, full std. fuel: 377 lb
Wingspan: 27 ft. 5 in
Overall length: 23 ft. 4 in
Height: 7 ft. 11 in.
Wing area: 109 sq. ft
Wing Loading: 22.3 lbs./sq.ft
Power loading: 9.3 lbs./hp
Seating capacity: 3/4
Cabin width: 40 in
Cabin height: 36 in
Cruise speed, 75% power: 186 kt
Fuel consumption, 65% power: 12.4 USgph
Max range, 75% power: 800 nm
Max range, 55% power: 1040 nm
Vso: 57 kt
Best rate of climb, SL: 1700 fpm
Service ceiling: 21,370 ft
Takeoff ground roll: 820 ft
Takeoff over 50-ft. obstacle: 1610 ft
Landing ground roll: 790 ft
Landing over 50 ft. obstacle: 1610 ft
SF-260
Engine: Lycoming O-540-E4A5 or D4A5, 260 hp
Prop: Hartzell 2 blade CS 76 in
Wingspan: 27 ft 5 in
Wing area: 108.7 sq.ft.
Aileron area total: 8.5 sq.ft.
Flaps area total: 12.7 sq.ft.
Fin area: 8.05 sq.ft.
Rudder area: 5.38 sq.ft.
Tailplane area: 14.9 sq.ft.
Elevator area: 10 sq.ft.
Length: 23 ft
Height: 7 ft 7 in
Wheel track: 7 ft 5 in
Wheel base: 5 ft 3.5 in
Tire size mains: 6.00 x 6
Tire size nose: 5.00 x 5
Seats: 3
MTOW normal: 2430 lb
MTOW aerobatic: 2095 lb
Empty wt: 1488 lb
Useful load: 937 lb
Wing loading: 22.4 lb/sq.ft
Power loading: 9.3 lb/sq.ft
Fuel cap wing total/useable: 26 /25.4 USG
Baggage capacity: 90 lb
Fuel cap tip tanks total/useable: 38 /36.6 USG
Max cruise SL: 230 mph
Range max cruise 30min res: 1275 sm
75% cruise fuel burn: 19 USG/hr
60% cruise fuel burn: 14 USG/hr
Stall: 65 mph
Vy: 125 mph
ROC SL: 1880 fpm
Service ceiling: 21,235 ft
Take off ground roll: 790 ft
Landing ground roll: 790 ft
Landing over 50ft obst: 1610 ft
SF.260C
SF.260D
Engine: Textron Lycoming O-540-E4A5, 260 hp (194 kW).
Rear seat load limit: 260 lb
Max cruise@ 10 000 ft: 186 kts.
Max range: 1,100 nm
SF.260E
SF.260M
SF.260TP
Engine: 1 x Allison 250-B17D turboprop, 350 shp (261 kW).
Span: 8.35 m
Length: 7.4 m.
Wing area: 10.1 sq.m
Empty wt: 750 kg.
MTOW: 1300 kg.
Warload: 300 kg.
Max speed: 380 kph
Initial ROC: 660 m / min.
Ceiling: 8500+ m
T/O run: 300 m.
Ldg run: 305 m
Fuel internal: 235 (+144) lt.
Range: 950 km
Endurance: 3hr 20min.
Combat radius lo-lo-hi: 150 km
SF.260W Warrior
Max take-off weight: 1300 kg / 2866 lb
Loaded weight: 830 kg / 1830 lb
Wingspan: 8.35 m / 27 ft 5 in
Length: 7.1 m / 23 ft 4 in
Height: 2.41 m / 8 ft 11 in
Wing area: 10.1 sq.m / 108.72 sq ft
Max. speed: 305 km/h / 190 mph
Ceiling: 4480 m / 14700 ft
Range w/max.fuel: 1715 km / 1066 miles
Armament: 300kg on underwing pylons
SIAI Marchetti S.211
Probably the first trainer to employ a supercritical wing section, the intention of the private venture design was to combine low unit cost with advanced technology and utilising the PWC 1T15D turbofan.
The first prototype of SIAI Marchetti’s S.211 two-seat basic trainer powered by a single Pratt & Whitney JT15D4C turbofan of 2,500 lb (1134 kg) was flown on 10 April 1981 at Milan-Malpensa airport with Siai Marchetti’s chief test pilot, Cmdte Alessandro Ghisleni, at the controls. Five further flight tests were made during the following week.
The type was being developed as an “attack optimised” trainer with a light¬weight HUD and navigation computer in association with the Republic of Singapore Air Force.
Also under test in a production S.211 was the 5 version of the JT15D, offering 3190 lbs thrust with a dry weight 50 kg more than the -4C fit.
An S.211A was test flown with a PWC JT15D 5 turbofan, providing 3200 lbs of thrust (2500 lbs from the 4C) for an additional 50 kgs of dry weight. As well as the 28 percent in¬crease in thrust, designed to make the S.211A more competitive with close contender MB339 at the top end of the scale, the aircraft has a stronger wing and a greater fuel capacity, boosted to 1440 lbs. The reinforced wing structure is to +7.33 and 3G’s.
Singapore Aircraft Industries (SAI) continues to assemble S.211 single-turbofan two seat basic trainers for the Rebublic of Singapore Air Force, which has ordered 30 aircraft, in 1987. Six of these were delivered in CKD form for reas¬sembly by SAI, while the remainder are being delivered in kit form for complete assembly in Singapore. Haiti is the only other confirmed customer for the S.211.
Siai-Marchetti (as part of the Agusta group) teamed with Grumman as a contender for the USAF’s PATS (Primary Aircraft Training System) requirement for a lightweight, low-cost basic trainer and attack aircraft.
Customers to 1990 were the Philippines (18), where the type is being assembled by PADC, Singapore (30), where a similar arrangement involves SAI, Haiti (4) and Uganda (4).
In 1990 the PADC in the Philippines started assembling S 211s, followed by SF 260 TPWs and SF 600 Canguro in agreement with SIAI Marchetti of Italy.
It can carry external loads of four underwing pylons although the difference between clean gross weight and maximum take off weight is only 1323 lb with the -4C engine.
S.211
Engine: 1 x Pratt & Whitney Canada JT15D-4C turbofan, 2,500 lb st (1134 kgp)
Span: 8.43 m / 28 ft 8 in
Length: 9.5 m / 31 ft 7 in
Wing area: 12.6 sq.m / 135.63 sq ft
Height: 3.8 m / 12 ft 6 in
Empty wt: 1645 kg
MTOW: 3100 kg
TO wt clean: 6000 lb
Warload: 660 kg
Max speed: 452 kt, 667 kph / 413 mph
Initial ROC: 1280 m / min
Ceiling: 12,200 m / 40000 ft
T/O run: 390 m
Ldg run: 360 m
Fuel internal: 800 lt
Range/Endurance: 2480 km / 3hr 50min
Combat radius hi-lo-hi: 550 km
Hardpoints: 4
Loading limit: 3.5G
Fuel burn: 700 lbs/hr
Ejection seat: zero/zero
Crew: 1-2
