Timber Tiger Aircraft Ryan ST-L

Nick Pfannenstiel, founder of Timber Tiger Aircraft, in February 2015, they decided to move forward with the Ryan project, a major life change. Nick acquired a set of original blueprints for the ST and started working backwards from the drawings. His goal was to maintain the Ryan’s appearance while incorporating technical improvements. Trimming the aircraft’s size by just 5% provided the needed dimensions to work with numerous options and keep things manageable. The scaled-down Ryan ST was designated the ST-L.

While the ST-L utilizes a semimonocoque fuselage like the original, the internal structure was redesigned from the ground up. There is a central steel bulkhead, which acts as the keystone for all of the aerodynamic stresses. This is heat treated after welding for strength. Steel wing stubs and landing gear complete the central attachments. Otherwise, the fuselage is composed of aluminum bulkheads and longerons. In order to preserve the Ryan’s pleasing lines, all bulkheads are positioned in the same locations as the originals. Other aspects of the airframe, including the tail feathers, wings and landing gear, also flow together nicely and fit the 95% scale replica perfectly.

Although it is 5% smaller than the ST, the ST-L actually has more room in the cockpit. “To create more space, we moved the rudder pedals to either side of the front seat rather than keeping them behind the seat like the original,” explained Nick. “So far, people up to 6 feet 5 have fit comfortably.”

For the wings, an aluminum spar was used in place of the wood spar found on the ST. The airfoil was changed from the original NACA 2412 to a Riblett GA30U-612, like that of the Kitfox. The ribs are a bonded aluminum honeycomb, which provides added strength while saving weight, and they are coated with an epoxy primer for corrosion protection. The wings are covered with Superflite, and the paint is from Stewart Systems. For simplicity, the drag/anti-drag wires were switched to a drag truss.

The Ryan ST has a reputation for being squirrelly on landings, mostly because of the leading-link landing gear. This was replaced with a torque-link landing gear, making ground handling much easier.

Because the ST-L was specifically designed to look as much like a real ST as possible, small details can make a big difference. Giving the illusion that a Menasco Pirate engine is lurking under the cowl is a four-pipe exhaust stack, although only two of the pipes actually do the job. Looking at the landing gear fairings, you can’t help but notice the mock rivets that help preserve the appearance of the original spats.

The handcrafted cow is formed by David and Maxwell Wenglarz at Wings Metal Work in San Pierre, Indiana.

At the end of construction, the ST-L came in 200 pounds lighter than the original ST.

The decision was made to go with a 100-hp Rotax 912 ULS, which fit perfectly under the cowl and has performed wonderfully in the prototype.

The ST-L kit is set up to create a natural progression where building one component naturally flows into the next. Starting with fuselage bulkhead Number 2, for example, the steel components are assembled first and everything else is added to this core. Structures and skins are predrilled where possible, but the tapered skins preclude predrilling all of the pieces. The builder will need to make a jig to build the fuselage. However, this is not required with the fully riveted quickbuild option.

Aluminum components are riveted into place using either solid or pulled rivets. For aesthetic reasons solid rivets are encouraged. The tail is composed of ribs attached to tubing, just like the original ST.

The wings can be constructed on a flat table and act as their own jig. Control cables have been replaced by push-pull tubes, and changes to the ST-L structure make wing rigging significantly easier than it was with the original ST. Other wing modifications include the change in airfoil and landing gear geometry, the addition of hydraulic toe brakes, simplification of the landing gear shock absorbers and using wire attachment fittings at the lower landing gear.

The finishing kit includes the handcrafted metal cowl to maintain the lines of the ST, as well as the firewall ring. The wheel pants and fairings for the gear legs, wing roots, stabilizer, rudder, gas cap and windshield are all fiberglass but can be made of aluminum if desired.

Build time is estimated at around 1500 hours for the standard kit, with significant time savings if the quickbuild fuselage option is selected. As of 2021, the estimated average cost to build is $75,000 to $90,000, but the price will vary from plane to plane depending on the engine and other options.

Timber Tiger ST-L
Powerplant: Rotax 912 ULS, 100 hp
Propeller: Performance Propeller, wood
Wingspan: 28.5 ft
Clipped wing option (6G limit): 1160 lb
Maximum gross weight: 1420 lb (1320 lb LSA)
Typical empty weight: 815 lb
Typical useful load: 605 lb (505 lb LSA)
Fuel capacity: 17.2 gal
Full-fuel payload: 502 lb (402 lb LSA)
Cruise speed: 80–113 kt
Climb rate (solo at 8000 ft): 800 fpm
Stall speed: 40 kt
Landing speed: 40–45 kt
Seating capacity: 2
Kit price: $42,700
Estimated completed price: $75,000–$90,000
Estimated build time: 1500 hr

Tilbury SF-1 Flash

Tilbury SF-1 NR12931

Designed by Owen Tilbury, the 1932 SF-1 Flash was a racer for the Nationals registered NR12931 and piloted by Art Carnahan.

It was stored in a barn in 1935, recovered in 1975 and restored by the Bloomington (IL) EAA Chapter, to go on exhibit at the McLean County Museum of History in Bloomington.

Engine: Church-Henderson, 45hp
Wingspan: 14’8″ (later increased to 17’10”)
Length: 11’10” (later 12’5″)
Seats: 1

Tijuana Aircraft Co Tijuana / BC-1 / BC-2 / BC-3

William Waterhouse was a respected structural analyst and engineer who “… undertook an assignment late in 1927 for the Mexican Government, which wanted to [produce] its own aircraft. Two monoplanes were constructed by Tijuana Aircraft Co, headed by Gov Abelardo Rodriquez of Baja California. Plans were furnished by the Mexican War Department and adapted by Waterhouse.

The planes, completed in early 1928. In test flights of the first, an observation type, a German BMW engine was used, but the second ship, expected to carry 380 gallons of fuel and make a non-stop flight to Mexico City, was scheduled for a Wright Whirlwind.”

It was flown by Luis Farell Cubillas, who on 8 March 1928 took off from the Tijuana factory enroute to Mexico City. The temporary-fitted 185hp BMW IIIa quit between Hermosillo and Navajoa, and Farell crash-landed on mountainous terrain. He was uninjured but the BC-1 was destroyed.

Tijuana BC-1 BMW installation

An article in Air Pictorial 27/2 by Jose Villela Jr, showed a photo of a parasol monoplane with a 185hp BMW, except the observer’s cockpit has been replaced with the pilot’s cockpit and power is a radial engine. That ship had “BC-2” on its Waterhouse-like vertical tail, and “BAJA CALIFORNIA” painted on the rear fuselage; photo caption: “Col. Fierro in ‘Baja California No. 2’ lands in the Canal Zone after his flight to Panama in 1928.” In his article Villela says, “Later Colonel Roberto Fierro in the Mexican-built ‘Baja California 2’ made the first non-stop flight between Mexico City and Havana in 14 hours, 50 minutes.”

The rear cockpit looks like it has a ring for a machine gun.

Tijuana BC-2

There was a later BC-3 described in Wagner’s article with a photo that has a family resemblance to the others, including the Waterhouse vertical tail.

BC-1
Engine: 185hp BMW
Wingspan: 43’0″
Length: 30’0″
Max speed: 122 mph

BC-2
Engine: Wright J-5C
Wingspan: 46’6″
Length: 28’6″
Max speed: 136 mph
Stall: 48 mph
Seats: 1

BC-3

Tijonrarov / Vaxmistrov Zhar-Ptitsa-2 / Konsomolskaya Pravda

The “Zhar Ptitsa-2” glider was designed by MK Tijonrarov, V. S. Vaxmistrov, and A. A. Dubrovin as a record-setting single-seater monoplane. In general, it was an improved development of the previous “Zhar-Ptitsa”. The main differences were in their slightly larger dimensions.

The Tijonrarov / Dubrovin “Zhar-Ptitsa-2” (Russian: Тихонравов / Дубровин / Вахмистров «Жар-Птица-2») participated in the VI national glider competitions, along with the other members of the “Zhar-Ptitsa”, “Skif” and “Gamayún”.

In the course of the competition and piloted by KM Vienzlav, he set a new national record by reaching 34.8 km in return flight.

The “Zhar-Ptitsa-2” glider would be presented again in the VII national competitions, developed in 1930.

Zhar-Ptitsa-2
Wingspan: 14.5 m
Wing area: 16.0 m²
Aspect ratio: 13.1
Empty weight: 160 kg
Wing loading: 14.4 kg / m²
Horizontal plane surface: 2.3 m²
Empennage surface: 1.15 m²
Glide ratio: 20.8
Accommodation: 1

Tijonrarov / Vaxmistrov Zhar-Ptitsa

The Tijonrarov / Dubrovin / Vaxmistrov “Zhar-Ptitsa” (Firebird) (Russian: Тихонравов / Дубровин / Вахмистров «Жар-Птица») glider was designed in 1927 by MK Tijonrarov and AA Dubrovin in order to participate in the IV National Competitions Gliding, which took place in that year. Later this group would be joined by fellow student VS Vaxmistrov.

The “Zhar-Ptitsa” glider was designed as a single-seat monoplane with a cantilever wing in parasol. The structure was built in wood. The wing was fixed to the fuselage at three points on a 200 mm base pile, made as a continuation of the central structure of the glider. The centroplane had a rectangular shape and in the area of union with the fuselage it was covered with 3 mm plywood.

The wing consoles featured a single spar structure and plywood covering from the leading edge to the spar area. From then on, the covering was made of fabric. The fixation to the centroplane was carried out by means of two screws. Assembly of the glider at the flight site could be done in 10-15 minutes.

The fuselage was spindle-shaped with a tapered bow and tail. Its structure consisted of trunk-type frames linked together by light stringers.

The tail unit was of the conventional monoplane type with the rectangular empennage.

The landing gear consisted of a ski. On takeoff (towed), the aircraft was tied to the tugboat by means of a 100-meter, 5-mm diameter rope that ended in a 3-meter-long and 188-mm thick rubber band. A hook was located at each end. For takeoff, the plane was attached to a trolley that detached when it reached takeoff speed. After separating from the glider, the tow plane dropped the rope. The landing was made by landing on the ski.

The “Zhar-Ptitsa” was completed in the workshops of the Air Fleet Academy and presented in Koktebel by the trio of developers.

This glider was quite successful, to the point of becoming the “passport” of the next competitions. In order to participate in the tests, the glider pilots had to make a previous flight in the “Zhar-Ptitsa”.

The main deficiency of the “Zhar-Ptitsa” glider was its incorrect centering as a result of the increased weight of the wood used in relation to that of the project. To correct this defect it was necessary to place a weight of 10 kg in the forward part of the fuselage.

The official opening of the IV National Sailing Competition was held on 18 of September of 1927, but since dawn that day strong winds that prevented flying. However, later, the force of the wind abated and it was allowed to compete. The “Zhar-Ptitsa” piloted by KM Vienslav flew for 15 km, landing on the outskirts of Feodosia, setting a new record.

Only 10 gliders appeared at the V National Sailing Competition held in Koktebel between September 23 and October 2, 1928. During the development it was clear that the main results of the contest would be distributed among the “Zhar-Ptitsa” gliders and its derivative “Gamayún”. During one of the flights, VA Stepanchonok achieved an excellent altitude making spirals in the “Zhar-Ptitsa”, but the expected records were not reached as the glider was damaged when landing with a tailwind.

The “zhar-Ptista” would participate again in 1929 in the VI annual National Sailing Competitions. On this occasion, it was used mainly in training tasks for glider pilots and its mastery was a determining factor in being able to fly in the competition.

The starting point of the competitions in Koktebel was located on the top of the Uzun-Syrt Mountain and featured a piece of steel buried in the earth. Before the start the glider was fixed to this structure. For the launch, a rubber strip was used that at one end had a hook and at the other ended in two 5-meter ropes. The hook was attached to a piece on the glider, while 4 or 5 people began to pull the other end. After advancing about 20 – 30 steps, a good tension was achieved on the tape. At that moment the pilot, located in the cockpit, released the glider, which would shoot like a stone to get up from the ground up to about 25 – 30 meters high. This was enough for a pilot with some training to be able to take advantage of a current of air or a thermal to take the necessary height and perform the glide.

In those early days the important thing for the pilots was not to return to the starting point or even to the base of the mountain. The greatest attention was paid to being able to achieve takeoff after launch at 30 meters high and being able to glide to the base of the mountain without damaging the aircraft or themselves. Means to transport the devices did not exist there. The glider was climbed to the top of the mountain, on shoulders, with the help of volunteers who came to support the pilots and the spectators themselves.

These volunteers were also in charge of helping with the repairs that had to be carried out on the gliders. Generally, as a reward, these volunteer helpers were “paid” by allowing them to fly in the gliders.

During the IV National Sailing Competitions, one of these active volunteers was the Kiev Polytechnic Institute student Sergei Korolyov, who came to realize his childhood dream of flying. Sergei Korolyov took flight for the first time on board the “Zhar-Ptitsa”.

One of the most experienced pilots of the VMF military pilot school located in Kacha was Vasili Stepanchonok, who in 1930 proposed taking off on gliders towed from other aircraft and developed a variant of the towline. This initiative was supported by the school principal Robert Rataush. On 3 May 1931, for the first time in the USSR, there was a takeoff of a glider towed by a U-1 (copy of the Avro 504K ) airplane. The glider used in this flight was the “Zhar-Ptitsa”, piloted by Maxim Moiseyev. Three subsequent flights were made by Mikhail Nyuxtikov, Gury Gribakin and Robert Rataush himself. Initially, this type of take-off was considered a kind of trick, but its importance from the sporting and military point of view was soon understood.

Nyuxtikov had received this glider as a gift after his outstanding performance as a test pilot at Koktebel competitions in 1930. To carry out the take-off with a ttowplane, Nyuxtikov proposed to develop a wheelbarrow on which the glider was located and which would detach at the time of take-off. For the first time in the USSR this system was used and possibly it was also one of the first uses in the world. In the magazine “ Samoliot ” of 1931 the details of this truck used for the take-off of the “Zhar-Ptitsa” were published.

Zhar-Ptitsa
Wingspan: 11. 5 m
Wing area: 16.3 m²
Aspect ratio: 12.9
Length: 6.93 m
Height: 1.9 m
Empty weight: 172 kg
Wing loading: 15 kg / m²
Elevator area: 2.6 m²
Rudder surface area: 0.85 m²
Spoiler area: 2.92 m²
Accommodation: 1

Tijonrarov / Vaxmistrov Skif-2

After finishing his studies at the VS Air Fleet Academy, Vaxmistrov went on to work at the NII VVS, where he developed his composite aircraft projects known as “Zvenó”. Upon completion of AA studies, Dubrovin went on to work at Factory No. 39 in Moscow and later as principal builder at Factory No. 301 in Khimki.

Tijonrarov in 1930, with the degree of military engineer of the second degree, was transferred to the TsKB of Factory No.39 Menzhinski where he led a motorization group.

Before saying goodbye forever, this trio of aeronautical builders designed a new glider that saw the light in 1931 under the name “Skif-2” (Russian: Тихонравов / Дубровин / Вахмистров “Скиф-2”).

The main objective of the “Skif-2” was to test the Pr-652 wing profile in flight. The new wing using this profile had been designed by AA Dubrovin and BN Sherementiev in 1930.

The “Skif-2” glider was designed as a single-seat monoplane with a cantilever wing in parasol. In general, it was an enlarged development of the successful “Skif”.

The structure was built in wood. The “Skif-2” incorporated a wing with double spar and wingspan increased to 17.2 meters, aspect ratio of 17.7 and a new Pr-652 profile. The wing was attached to the fuselage at three points on a central pile built as an integral part of the fuselage support structure. The centroplane had a rectangular shape and in the area where it joined the fuselage it was covered with 3 mm plywood. The wing was covered with plywood up to the position of the second spar. From then on, the covering was made of fabric.

The fuselage on the “Skif-2” remained unchanged and featured a spindle shape with a tapered bow and tail. Its structure consisted of trunk-type frames linked together by light stringers. In the rear part of the fuselage the tail unit was located was of the conventional monoplane type and in the lower part the landing ski.

The pilot was located in a closed cockpit, which had a removable celluloid cover and two small windows located at the level of the pilot’s eyes. The cockpit had so much space that the pilot could sit with his parachute. The cover provided the necessary clarity to allow the pilot to see the instrument records.

The “Skif-2” glider participated without great success in the VIII National Sailing Competitions held in Koebel . The new wing construction was 12 kg heavier than the base model, which affected the practical results of the glider. On the other hand, most of the flights were carried out without the cockpit cover, so the coefficient of aerodynamic drag rose from 0.094 to 0.115.

In general, the performance of the “Skif-2” was inferior to the “Skif”. The aerodynamic quality decreased from 22.3 to 20 and the descent speed increased from 0.7 m / s to 0.72 m / s. Due to the repair work carried out, the “Skif-2” was able to start racing late accumulating only a poor value of 20 flight hours.

Skif-2
Wingspan: 17.2 m
Wing area: 16.7 m²
Aspect ratio: 17.7
Empty weight: 200 kg
Wing loading: 16.8 kg / m²
Stabilizers surface: 2.6 m²
Elevator area: 1.24 m²
Spoiler area: 3.8 m²
Glide ratio: 20
Descent speed: 0.72 m / s
Accommodation: 1

Tijonrarov / Vaxmistrov Skif

Dubrovin, Vaxmistrov, Yumashiev, and Tijonrarov alongside the Skif glider in 1929.

Despite being serving in the “Lenin” squad, Tijonrarov did not cease his constructive activity. During 1928, together with VS Vaxmistrov and AA Dubrovin, two new gliders were created, called “Gamayún” and “Skif” (Russian: Тихонравов / Дубровин / Вахмистров «Скиф»), both produced as a development of the excellent “Zhar-Ptitsa”.

The “Skif” glider was a development of the scheme of the “Zhar-Ptitsa” glider. It was designed as a single-seater monoplane with cantilever wing in parasol. The structure was built in wood. The wing was fixed to the fuselage at three points on a 200 mm base pile, made as a continuation of the central structure of the glider. The centroplane had a rectangular shape and in the area of union with the fuselage it was covered with 3 mm plywood.

In this model the builders decided to use a modified structure, which introduced a second stringer. The plywood overlay was extended to the position of this second spar. From then on, the covering was made of fabric.

The fuselage was spindle-shaped with a tapered bow and tail. Its structure consisted of trunk-type frames linked together by light stringers. Another significant difference from the design of the previous “Zhar-Ptitsa” and “Gamayún” models was the shape of the tail. The “Skif” featured new removable triangular-shaped surfaces with rounded ends. At the bottom of the fuselage was the landing ski.

The pilot was located in a closed cockpit, which had a removable celluloid cover and two small windows located at the level of the pilot’s eyes. The cockpit had so much space that the pilot could sit with his parachute. The cover provided the necessary clarity to allow the pilot to see the instrument records. The cockpit panel featured a speedometer, barometer, altimeter, lap counter and overload indicator. A thermometer and an angle of attack marker were located on the outside.

During the tests some vibration was noted in the rudder area, but it was soon resolved by reducing the area.

In 1929, during the VI National Sailing Competitions in Koktebel A. B. Yumashiev on the “Skif” glider set several national records.

On October 12, taking off from the south slope, near the afternoon, when the flights had already ceased, the pilot felt that the glider was staying well in the air and began to rise. When it exceeded 570 meters the barograph stopped recording. Yumashiev began gliding using the northwesterly wind and landed safely after covering a record distance of 13 km. This was the first time that a glide over a thermal flow with ascent over the plain was achieved in the USSR.

On October 22, Yumashiev would once again become the news when he reached a record height of 1520 meters on the “Skif”. After achieving that height, Yumashiev decided to try a new distance record, but his glider lost 600 meters in height quickly. With the remaining height, he managed to maintain a linear flight until reaching Dalnie Kamishi village, located at 27.2 kilometers.

The “Skif” glider would be presented again in the VII edition of the national competitions, held in 1930.

Skif
Wingspan: 16.0 m
Wing area: 16.0 m²
Aspect ratio: 16
Empty weight: 170 kg
Wing loading: 15 kg / m²
Horizontal plane surface: 2.3 m²
Empennage surface: 1.15 m²
Glide ratio: 22.2
Accommodation: 1

Tijonrarov / Vaxmistrov Gamayún

Despite being serving in the “Lenin” squad, Tijonrarov did not cease his constructive activity. During 1928, together with VS Vaxmistrov and AA Dubrovin, two new gliders were created, called “Gamayún” (Russian: Тихонравов / Дубровин / Вахмистров «Гамаюн») and “Skif”, both produced as a development of the “Zhar-Ptitsa”.

The “Gamayún was designed as a record-setting single-seater glider and was obtained as a development of the “Zhar-Ptitsa” glider and was generally similar to it. The main difference of the “Gamayún” consisted in the increase of the wingspan. Other minor modifications included changes in the fuselage structure and variation in the centering to overcome the difficulties of the “Zhar-Ptitsa”. These modifications hardly brought improvements in the results.

These skills developed in Koktebel between 23 September and 2 October 1928 as 10 gliders were presented in the V National Sailing Competition. The “Gamayún” was one of the copies that were released in this contest. Already during the development, it was clear that the main results of the contest would be distributed between the “Zhar-Ptitsa” and the “Gamayún” gliders.

The “Gamayún” piloted by test pilot, major general of aviation, Andrei Borisovich Yumashiev, made several flights. In the competition he showed the best results, setting two national records: the one for a straight-line range of 14 km and the one for height above the take-off point of 375 meters. This flight lasted 1 hour and two minutes on the Uzun-Syrt path to Sorogol (near Feodosia). The landing at Sorogol was carried out in a small space between the coastline (one wing of the glider was left in the water) and some railroad warehouses. Yumashiev tried to fly in the opposite direction without success, but was forced to land in the market place to the great rejoicing of the local population.

With this flight the record attempts of that year would end.

The “Gamayún” participated in the VI edition of the national glider competitions. Piloted by Sergueyev, it was approaching landing when a gust of wind threw it abruptly upwards. As a result of these abrupt manoeuvres, the wings were detached from the fuselage. The fuselage fell to the ground, but the pilot was unharmed.

Gamayún
Wingspan: 16.0 m
Wing area: 17.0 m²
Aspect ratio: 15
Empty weight: 153 kg
Horizontal plane surface: 2.3 m²
Empennage surface: 0.85 m²
Ailerons area: 2.10 m²
Wing loading: 13.4 kg / m²
Accommodation: 1

Tijonrarov / Vaxmistrov AVF-22 Zmiei Gorinich

Shortly before graduating, in 1925 at the Zhukovski Military-Aeronautical Engineering Academy, Tijonrarov, together with the first-year student VS Vaxmistrov, designed and built the AVF-22 glider and that Tijonrarov nicknamed “Zmiei Gorinich” (Russian: Тихонравов / Вахмистров АВФ-22 “Змей Горыныч”).

The AVF-22 “Zmiei Gorinich” glider was designed as a monoplane with a high trapezoidal cantilever wing of conventional design. The structure was built in wood with a textile covering. The large wings featured large ailerons on the trailing edge of the wing. The tail unit was a monoplane type with an integral rudder.

The fuselage was constructed of plywood with a rectangular cross section. In its side view, the fuselage was shaped like a wing aerodynamic profile. The tail unit was a monoplane type with a rectangular-shaped integral rudder and trapezoidal-shaped horizontal planes.

The landing gear consisted of a pair of skis in the lower region of the fuselage.

After graduating from the Academy, Tijonrarov was sent to serve in the “Lenin” Squad. Vaxmistrov and his glider were entered in the glider competitions held during August 1925 in Renske, Germany.

Specialists and the German press were greatly interested in the “Fire Dragon” (translation given to the name of the glider in Germany). On August 29, pilot Vladimir V. Sergueyev achieved a flight in the AVF-22 of 4400 meters. A day later the pilot LA Jungmeister managed to reach the height of 265 meters, which was a record for the time. On that very second day of racing, VV Sergueyev managed to fly the “Zmiei Gorinich” a distance of 11 km.

The glider “Zmiei Gorinich” participated in the III National Sailing Competitions held in Koktebel between September 27 and October 11, 1925. During its first flight in this contest the glider lost speed and fell, hitting the ground. The pilot received a major trauma to the neck. The glider could not be rebuilt.

AVF-22 “Zmiei Gorinich”
Wingspan: 14.35 m
Wing area: 19 m²
Length: 6.96 m
Height: 1.8 m
Empty weight: 130 kg
Wing loading: 11 kg / m²
Elevator area: 2.23 m²
Rudder surface area: 1.3 m²
Ailerons area: 1.0 m²
Wing elongation: 10.8
Accommodation: 1