Polikarpov BDP

The 23 of January of 1940 the Commissariat of Aviation Industry created the Directorate for creating landing gliders. In the autumn of that year, in an extraordinary meeting, with the presence of Stalin, the decision was made to launch a competition for the development of airplanes of this type and their series production. The best would be mass-produced and used successfully in operations during the Great Patriotic War.

Nikolai Polikarpov had no experience in glider design, so he did not participate in the competition. Despite this, at the beginning of June 1941 its construction bureau, unexpectedly for many, presented a project for a landing glider. The production of gliders was carried out not in aviation factories, but in carpentry and furniture factories.

The Polikarpov glider was designed as an aircraft to support penetration units. After analyzing the losses of the Germans during the landing operations, the Soviet aircraft manufacturer came to the conclusion that it was possible to reduce them by using well-protected and armed means of landing. To achieve this objective, he designed a glider from which the landing troops, before launching themselves, could direct fire against enemy positions, using their light weapons. The protection of the device was obtained through the use of removable armoured plates, which once landed the glider allowed to create a defensive barrier for the soldiers.

The new glider was named BDP (Russian: Поликарпов БДП), after Boyevoi Disantni Planior or Military Landing Glider.

The BDP landing glider was desiigned as a high-wing monoplane with a 20-meter wingspan and an aerodynamically designed fuselage. The entire construction was made of wood.

Designers put special emphasis on making an airplane cheap and easy to produce. Due to its dimensions, the BDP was capable of transporting 16 soldiers with their equipment and its towing had to be carried out by Túpolev SB or Ilyushin DB-3 bombers. The fuselage was entirely made of wood. The pilot had an emergency cover with a structure also in wood. To improve visibility during landing, the lower part of the cab was glazed.

The landing troops sat on benches located on the sides of the fuselage, forming part of the structure. Between the two rows of benches there was a 600mm corridor. The exit of personnel and cargo was carried out through two 900 x 950 mm doors, one located in the front region on the right and the other in the rear on the left. In the first BDP copy there were two small doors on the right and two on the left.

In the lower part of the fuselage, behind the cargo area, a hatch was prepared to parachute from the glider.

The wing of the BDP was made of wood and had a single spar. The coating of the leading edge and the force points was done with plywood. The rest of the wing was covered with fabric. The wing profile used was the NACA 230. In order to reduce the landing speed in the section between the ailerons and the fuselage, Shrenk-type flaps were installed.

In the area of the leading and trailing edges of the wing, special hatches were located to allow firing with light weapons, covering the upper hemisphere. To defend the tail a section of the upper rear fuselage could be raised and become a firing point for the gunner.

The tail was monoplane and cantilever, constructed of wood covered with plywood and fabric.

The landing gear consisted of two ash skis placed on leaf springs to absorb the impact. The junction of the skis and the fuselage was covered by fabric covered fairings. For landing the BDP used a 400 x 150 mm four-wheel detachable wheelbarrow.

The glider did not have its own weapons, but did have attachment points for seven DP-type infantry machine guns. Two machine guns could be installed to defend the upper hemisphere, one in the lower hatch and two on the sides.

Inside the fuselage were 12 5.5 mm armored plates with dimensions of 480 x 550 mm. The pilot had armor on the back of the seat. All this protection added 127 kg to the weight of the glider.

The development of the BDP project was carried out by Polikarpov and his collective during the month of June 1941.

The project was approved by the NKAP management and it was decided to carry out the construction of the prototype at Factory No.51.

By the end of the summer of 1941 the glider was finished and ready for flight tests. The first flights were carried out in September and took place from the LII airfield in the Moscow suburbs. As a tug, an SB bomber with M-103 engines was used. The glider was piloted by VP Fyodorov.

Only 14 flights were made, which were interrupted on October 14 due to the advance of the Germans and the beginning of the evacuation.

First BDP copy during tests near Moscow in September 1941.

As a result of the tests, defined as inconclusive, it was concluded that the BDP was stable in flight and that it could be maintained with free controls. The effectiveness of the rudders was acceptable, both during flight and on landing. The piloting technique was simple and did not demand a great qualification from its pilot, which ensured its control by pilots who had flown training gliders.

The negative aspects were the lack of structural strength at various points on the wing and fuselage. This caused that during the tests the flight weight was limited to only 2200 kg and the speed up to 220 km / h (the glider having been calculated for 3200 kg and 320 km / h respectively). The pilot pointed out that the curved glass in the windshield distorted the vision and proposed to replace it with a normal one made of straight pieces. When the aerodynamic brakes were extended, there was creaking in the tail area.

It was recommended to work on solving these problems and then present the model for series production. In relation to this process, there were no difficulties, since the construction could be carried out in carpentry with basic equipment. TsAGI specialists warned that the production cost of the Polikarpov model exceeded that of other similar gliders.

This first specimen was evacuated by air in October 1941 to the west. Curiously, during the flight of this unknown aircraft towed by an SB bomber, a group of fighters from Moscow’s anti-aircraft forces (PVO) went out to intercept, forcing the glider to land near Kashira. The glider was looted by the local inhabitants and in that condition it was returned to Moscow shortly thereafter.

The second specimen, called BDP-2, was built in Novosibirsk, where Factory No. 51 in Moscow and the KB in Polikarpov were evacuated.

The glider was delivered for testing to the LII affiliate on February 6, 1942 and flown by II Shelest.

The BDP-2 presented a reinforced construction in relation to the original model, which brought with it a certain increase in weight. Externally it was also something different. The pilot’s windshield featured flat glass pieces and various elements were simplified. The trailing edge of the height and steering rudders was made by means of a steel cable as was the style in the first Soviet aircraft.

The tests of the BDP-2 with ski landing gear lasted until March 14, 1942. During this time several attempts were made to lessen the problem of tail creaking. The results improved after drilling a series of holes in the aerodynamic brakes, thus reducing the turbulence of the airflow.

Second BDP-2 prototype tested in Novosibirsk in the winter of 1941 – 1942.

The test conclusions again emphasized the simplicity of the piloting, the high payload capacity, good manoeuvrability and stability in different centering regimes. Serial production of the model was recommended.

Interior layout in the cabin of the BDP-2 glider.

Almost in parallel with the flight tests, the search began for a possible production base to develop series production. After reviewing various factories and companies in the region near Novosibirsk, it was decided to select the Siberian Military Region Workshops. These facilities had previously functioned as auxiliary production capacity for Factory No.153, dedicated to the manufacture of skis.

The first figures showed a number of 100 gliders with a unit cost of 41,125 rubles.

While negotiations were taking place, a new production site was defined. It was the Stalingrad Factory No. 490. In the middle of the summer of 1942 the plans and all the technical documentation were transferred there from Novosibirsk. Soon the military situation changed and the arrival of the Germans in Stalingrad thwarted production plans.

Along with the inability to produce in Stalingrad the opinion of the VVS was a lack of need to produce the BDP. The course of the war had shown little chance of success and there were already produced successful models A-7 of Antonov and G-11 of Gribovski.

In July 1942 the BDP-2 was destined to serve as a transport in the direction of the Moscow – Irkutsk air force. Several flights were carried out towed by a PS-40 (postal Ant-40) on the Novosibirsk – Omsk – Sverdlovsk route and vice versa. This route was also covered by several Antonov A-7s . The results of these experimental flights were impressive and it was proposed to build several examples of transport gliders for civil use with Aeroflot.

In 1943, at Factory No.51, the assembly of 10 copies of the BDP began. It is known that until the end of the year only two copies had been delivered. A third and fourth specimens were 98% complete, the fifth at 80%, the sixth at 28%, and the seventh only at 10%. No evidence has been found after that date.

Polikarpov, in an attempt to achieve full autonomy for the BDP, decided to develop a motorized model that was named MP. A prototype was successfully built and flown, but it was not mass-produced either.

Polikarpov BDP
Wingspan: 20.00 m
Length: 13.60 m
Wing area: 44.72 m²
Empty weight: 1470 kg
Normal weight: 3408 kg
Crew: 1
Payload Capacity: 16 Soldiers Equipped

Color scheme of the first BDP prototype without the ski train fairings.
Color scheme of the second BDP-2 prototype.

Polikarpov TIS

To meet a requirement for a heavy escort fighter, or TIS (Tyazhely istrebitel soprovozhdeniya), formulated in the autumn of 1938, the Polikarpov OKB designed a low-wing monoplane of all-metal construction powered by two 1,400hp Mikulin AM-37 engines. Fixed forward-firing armament comprised four 7.62mm and two 20mm guns, rear protection being provided by single flexible 7.62mm guns fired from dorsal and ventral positions by the second crew member. The first prototype, Samolet A, was flown in September 1941, but evacuation of the Polikarpov facilities to Novosibirsk delayed the programme, and an improved second prototype, Samolet MA, was not flown until 13 June 1944. The MA was intended to be powered by 1,700hp Mikulin AM-39 engines, but their non-availability dictated installation of 1,665hp AM-38 engines. Fixed forward-firing armament was changed to two 37mm cannon and two 12.7mm machine guns. The flight testing of the MA was in its early stages when, on 30 July 1944, Polikarpov died and his OKB was almost immediately disbanded, the TIS programme being abandoned.

Max take-off weight: 7840 kg / 17284 lb
Empty weight: 5800 kg / 12787 lb
Wingspan: 15.50 m / 51 ft 10 in
Length: 11.70 m / 38 ft 5 in
Height: 4.35 m / 14 ft 3 in
Wing area: 34.85 sq.m / 375.12 sq ft
Max. speed: 555 km/h / 345 mph
Range: 1070 km / 665 miles

Polikarpov TIS

Polikarpov ITP

In 1941, the Polikarpov OKB began work on an Istrebitel’ Tyazhely Pushechny – heavy cannon fighter – which was to mount a 37mm cannon between the cylinder banks of a 1,650hp Klimov M-107P 12- cylinder liquid-cooled Vee engine, and also carry two synchronised 20mm cannon. The aircraft was of mixed construction, the fuselage being a wooden monocoque and the wing of steel and dural. The first prototype, referred to as the M-1, was completed in October 1941, but difficulties with the engine delayed the initiation of flight testing until 23 February 1942. An M-107A replaced the M-107P late in 1942, but engine difficulties were still experienced, and a second prototype, the M-2, was completed with an AM-37 engine of 1,400hp with which it flew on 23 November 1943. The M-2 had an armament of three 20mm cannon and eight RS-82 unguided rocket projectiles, the engine eventually being replaced by an AM-39 of 1,700hp. Factory flight testing continued until June 1944 when the programme was abandoned.

M-1
Max take-off weight: 3570 kg / 7871 lb
Empty weight: 2960 kg / 6526 lb
Wingspan: 10.00 m / 33 ft 10 in
Length: 8.95 m / 29 ft 4 in
Wing area: 16.45 sq.m / 177.07 sq ft
Max. speed: 655 km/h / 407 mph
Range: 1280 km / 795 miles

Polikarpov ITP

Polikarpov Po-2 / U-2 / RV-23 / E-23 / PZL Mielec CSS-13

The U-2TPK prototype, which appeared in early 1927 was designed by N.N.Pellyakov, had been built to achieve economy in repair and maintenance, the wings comprising four identical thick-section interchangeable rectangular panels with square tips. Similarly, a common control surface was used for ailerons, elevators and rudder. The result was a biplane with very poor flight characteristics. It had thus to be redesigned, appearing as a neat, manoeuvrable biplane having staggered single-bay wing with rounded tips, conventional cross-axle landing gear, and tandem open cockpits for instructor and pupil. Powered by a 75kW radial engine, the new prototype made its first flight on 7 January 1928. An immediate success, it was placed in quantity production, deliveries starting in 1928, and by the time of the German invasion of the Soviet Union in mid-1941 over 13,000 had been completed.

Polikarpov Po-2 Article

Though its principle role was primary training, the U-2 was soon modified as a light passenger transport, air ambulance and agricultural aircraft. Production continued on a massive scale during World War II, and the U-2 took on an even wider range of duties, including liaison, light attack, night nuisance raider and propaganda aircraft complete with microphone and loudspeaker.

The Russians organized an entire regiment of women pilots to attack German targets at night. Called Nächthexen, or “Night Witches,” by the Germans, they operated Po-2s.

Pilots of the 588th Night Bomber Regiment, aka the “Night Witches,” in 1944

On 3 March 1944 the German 1st Easrwen Squadron ( I.Ostfliegerstaffel) was transferred to Lida airfield near Vilna (Lithuania). This unit consisted of Russian volunteers who flew captured Soviet U-3 biplanes, they called ‘sewing machines’. The unit had been set up in Daugavpils (Latvia) in December 1943, and now its members flew operations in the zone of Luftflotte 6 under General Ritter von Greim. The observers on board he U-2s dropped small-calibre bombs by hand. The aircraft flew every night when visibility permitted, crossing over the Soviet lines with nuisance raids.

In time, the Po-2 set a record for a basic design: A grand total of some 40,000 were produced. The Soviet Union built Po-2s from 1928 to 1951, and Poland turned them out under license from 1948 to 1955. But that was not the end of it. Numerous aeroclubs and enthusiasts kept constructing them in Russia until 1959.

After Polikarpov’s death, on 30 July 1944, the U-2 was redesignated Po-2 in his honour, and post-war it continued in production in the USSR for several years. Trainer and ambulance variants were built on a large scale in Poland from 1948 to 1953, Po-2s served with many Soviet allies and a small number still remain in flying condition in the USSR and several other countries. The total built is credibly reported to be in excess of 40,000.

In 1947, the aviation of the People’s Army of Poland turned to the Polish aviation industry with an order to start serial production of the Soviet Po-2 training and liaison aircraft. In the USSR, it was agreed to sell its license and in 1948, the Central Aircraft Study in Warsaw, under the direction of Stanisław Lassota, the licensing documentation for the aircraft was prepared. The license version of the aircraft differed from the Po-2 prototype in a different type of ailerons, had a trim on the elevator, different shock absorber fairings and some on-board instruments, minor improvements in the airframe design, as well as an improved engine, so the designation was changed to CSS-13.

The production of the aircraft began at WSK-Mielec in December 1948. The prototype of the aircraft, SP-AKZ, made its first flight on December 18, 1948 and the pilots were Ludwik Lech and Kazimierz Tyrlik. In the following year, its testing was carried out at the Institute of Aviation in Warsaw. During the tests, it was found that the aircraft has good handling characteristics and behaved safely at take-off and landing.

In 1999, the first serial model was flown. Serial production of the aircraft lasted at PZL Mielec from 1949 to 1950, and then 1952-1956 at WSK Okęcie in Warsaw. In total, 560 CSS-13 aircraft were produced in the years 1949–1956, of which 180 at PZL Mielec and 380 at WSK Okęcie. Airplanes of this type, popularly known as “Pociaki” or “Papayas”, were used by military, agricultural aviation as well as by flying clubs.

The first new aircraft were directed to aviation units and military schools as early as 1949. In the first half of the 1950s, CSS-13 aircraft were the basic aircraft in squadrons and liaison keys of the air forces. The following versions were used: liaison equipped with a double control system, bomber with a sight glass in the lower right wing for targeting with a gunsight and bomb locks under the wing and placed on the top of the fuselage, behind the second cabin on a rack, a movable aircraft machine gun. In addition to the air force, CSS-13 aircraft were used in the aviation units of the Navy and in the Border Protection Forces to patrol the state border.

During 1953–1955, LOT Polish Airlines operated 20 CSS-13 aircraft adapted for agricultural purposes (dusting crops and forests). In the flying clubs, CSS-13 aircraft were used in the 1960s for pilot training, training flights, glider towing, and parachute jumpers transport.

CSS-13

In 1953, a prototype of the version of the CSS-13 aircraft was built and flown at the Okęcie airport in Warsaw, marked as CSS S-13, designed by Tadeusz Sołtyk, M.Sc. A total of 59 aircraft of this type were produced.

CSS-13 (serial number 8-0511), Museum of Polish Arms in Kołobrzeg

Dozens of them have been exported, e.g. to Romania and Hungary. The last copy was withdrawn from use in 1978.

A Polish-built ambulance version has a raised rear decking.

Gallery

Replica:
Rusavia Polikarpov U-2

Variants:

U-2: Basic model, built in large numbers as a two-seat primary trainer. It was also built in many different versions, both as civil and military aircraft. The U-2 variants also included a light transport, utility, reconnaissance and training aircraft. Power plant was the M-11 radial piston engine of 75 kW (100 hp). Later models were also equipped with uprated M-11 engines of 111 kW (150 hp). Some aircraft were fitted with a rear closed cabin, other were fitted with sledges or floats.

U-2A: Two-seat agricultural crop dusting aircraft, powered by an 86 kW (115 hp) M-11K radial piston engine. Later redesignated Po-2A after 1944.

U-2AO: Two-seat agricultural aircraft.

U-2AP: Agricultural aircraft, with a rear cab replaced with a container for 200–250 kg (441-551 lb) of chemicals. 1,235 were built in 1930–1940.

U-2G: This experimental aircraft had all the controls linked to the control column. One aircraft only.

U-2KL: Two aircraft fitted with a bulged canopy over the rear cabin.

U-2LSh: Two-seat ground-attack, close-support aircraft. The aircraft were armed with one 7.62 mm (0.30 in) ShKAS machine-gun in the rear cockpit. It could also carry up to 120 kg (265 lb) of bombs and four RS-82 rockets. Also known as the U-2VOM-1.

U-2LPL: Experimental prone-pilot research aircraft.

U-2M: This floatplane version was fitted with a large central float and two small stabilizing floats. Not built in large numbers. Also known as the MU-2.

U-2P: Floatplane version, built only in limited numbers, in several variants with different designations.

U-2S: Air ambulance version, built from 1934. It could take a physician and an injured on a stretcher on a rear fuselage, under a cover. Variant U-2S-1 from 1939 had a raised fuselage top upon the stretcher. From 1941 there were also used two containers for stretchers, that could be fitted over lower wings or two containers for two seating injured each, fitted under lower wings.

U-2SS: Air ambulance aircraft.

U-2ShS: Staff liaison version, built from 1943. It had a wider fuselage and a closed 4-place rear cab.

U-2SP: Civil transport version, could carry two passengers in open individual cabs, built from 1933. Other roles included aerial survey, and aerial photography. A total of 861 were built between 1934 and 1939.

U-2SPL: This limousine version was fitted with rear cabin for two passengers.

U-2UT: Two-seat training aircraft, powered by an 86 kW (115 hp) M-11D radial piston engine. Built in limited numbers.

U-2LNB: Somewhat like the earlier -LSh version, a Soviet Air Force two-seat night attack version, built from 1942. Armed with one 7.62 mm (0.30 in) ShKAS for rear defense, plus up to 250 kg of bombs under the wings for land support. Earlier aircraft were converted to improvised bombers from 1941.

U-2VS: Two-seat training and utility aircraft. Later redesignated Po-2VS after 1944.

U-2NAK: Two-seat night artillery observation, reconnaissance aircraft. Built from 1943.

U-3: Improved flying training model, fitted a 149 kW (200 hp) seven cylinder M-48 radial engine.

U-4: Cleaned-up version with slimmer fuselage; not built in large numbers.

  • (Total U-2 manufacture: 33,000)

Po-2: Postwar basic trainer variant.

Po-2A: Postwar agricultural variant.

Po-2GN: “Voice from the sky” propaganda aircraft, fitted with a loud speaker.

Po-2L: Limousine version with an enclosed passenger cabin.

Po-2P: Postwar floatplane version; built in small numbers.

Po-2S: Postwar air ambulance variant, with a closed rear cab.

Po-2S-1: Postwar ambulance version, similar to the pre-war U-2S.

Po-2S-2: Postwar ambulance version, powered by a M-11D radial piston engine.

Po-2S-3: Postwar ambulance version, which had two underwing containers, each one was designed to transport one stretcher patient. Also known as the Po-2SKF.

Po-2ShS: Staff communications aircraft, fitted with an enclosed cabin for the pilot and two or three passengers.

Po-2SP: Postwar aerial photography, geographic survey aircraft.

RV-23: This floatplane version of the U-2 was built in 1937. It was used in a number of seaplane altitude record attempts. The RV-23 was powered by a 529 kW (710 hp) Wright R-1820-F3 Cyclone radial piston engine.

CSS-13: Polish licence version, built in Poland in WSK-Okęcie and WSK-Mielec after World War II (about 500 built in 1948–1956).

CSS S-13: Polish ambulance version with a closed rear cab and cockpit and Townend ring (53 built in WSK-Okęcie in 1954–1955, 38 converted to S-13).

E-23: Research version, built in the Soviet Union in 1934, for research into inverted flight.

Engine: 1 x Schvetsov M-11, 74-118kW
Max take-off weight: 983 kg / 2167 lb
Empty weight: 740 kg / 1631 lb
Wingspan: 11.4 m / 37 ft 5 in
Length: 8.2 m / 27 ft 11 in
Height: 3.1 m / 10 ft 2 in
Max. speed: 146 km/h / 91 mph
Cruise speed: 100-130 km/h / 62 – 81 mph
Ceiling: 5000 m / 16400 ft
Range w/max.payload: 430 km / 267 miles
Crew: 1
Passengers: 1-2

CSS-13
Engine: M-11D, 125 hp (92 kW)
Wing span: 11,4 m
Wing area: 33,15 m2
Length: 8,17 m
Height: 3,1 m
Empty weight: 723 kg
MTOW: 1057 kg
Maximum speed: 150 km/h
Stall: 70 kph
Ceiling: 3000 m
ROC: 2.0 m/s
Range: 650 km
Armament: 1 x 7.62 mm ShKAS machine gun
Bombload: 300 kg

Polikarpov Po-2

Player

William Earl Player & Harry Thalman, Salt Lake City UT.

1940: Plxweve Aircraft Co div of Aero Industries
(pres: John Greenleaf)
620 W Olympic Blvd
Los Angeles CA.
USA

1941:
(pres: Ralph Hemphill)
5245 W San Fernando Rd,
Los Angeles
USA

Involved in the Greenleaf CT-6A

Platt-Le Page XR-1

In July 1940 the Platt-LePage Aircraft Co. won the competition to build a helicopter designated XR-1.

The first flight of the XR-1 took place in May 12 1941, a number of teething problems developed with the control system, causing delays in progress, along with test pilot Lou Leavitt refusing to fly the XR-1 in forward flight.

In June of 1943 Col. H.F. Gregory took the XR-1 up and proceeded to fly the XR-1 at speeds of up to 100 miles per hour, and completed the first close course flight of the XR-1. By the summer of 1943 the XR-1 was flying with much better control, when on July 4, 1943 the XR-1 was damaged in a crack up due to the loss of a rotor blade, further slowing testing.

XR-1A

In October 1943 the second model XR-1A made its first flight, and was found to have better flying characteristics than the XR-1. Numerous flight tests were carried out and by June of 1944 the XR-1A was flown from Eddystone Pennsylvania, to Wright field in Dayton Ohio, passing through a dangerous mountain pass and flying through a long stretch of bad weather, during which the XR-1A encountered a grounded Sikorsky SR-4 along the way.

By August of 1944 rebuilt XR-1 was back in the air and slowly progress was made in solving the control problems, In March of 1945 just a few days after a new control system was installed that solved some the problems with longitudinal stability, the Air Corps cancelled all contracts with Platt-LePage, including seven additional YR-1A helicopters that were to be built.

Platt-Le Page Aircraft Co

In 1935, due to the effects of the economic depression in the 1930’s, Dr .Wynn Laurence LePage left Kellett to become an independent engineer, by 1935, LePage met and became partners with Haviland H. Platt, a mechanical engineer and patent expert with a number of rotary wing patents. In 1938 W. Laurence LePage traveled to Germany to view the Focke Fw-61 helicopter, and after much negotiation obtained an option to build Focke helicopters in the USA, but the worsening conditions between the two governments prevented a deal going through.

In November of 1938, Platt and LePage formed The Platt-LePage Aircraft Company, and abandoned talks with the German government to import a Focke helicopter. They proceeded on their own to design a helicopter based on their patents and ideas.

Small size and lack of capital of Platt-LePage Aircraft, along with lack of orders for military aircraft caused the Platt-LePage Aircraft Co. to shut down in August of 1946. The McDonnell Aircraft Co. obtained most of the helicopter patents from Platt-LePage during the liquidation of the company, along with the personnel responsible for the twin engine project.

Pitts S-1

Pitts S-1-11B Super Stinker

Curtis Pitts began designing the single-seat S 1 in 1942. The 55 hp prototype flew in September 1944, but was repowered with 90hp Franklin and sold to a cropduster, who reportedly was so hard of hearing that one time he didn’t hear the motor quit and crashed—no injury, but the plane was written-off.

Pitts S-1 Article

A second Special, with 85hp Continental C-85, went to aerobat Betty Skelton in 1947 as Li’l Stinker (NX86401/N22E) (still active in 1975, displayed at NASM 2001).

Black Beauty (built by Pitts for Caro Bailey) started the trend toward more power by packing a 125 hp Lycoming O 290.

Betty Skelton Pitts Special

The Pitts Special is a single seat, open cockpit, fully aerobatic biplane. The fuselage is made up of a welded steel tube structure to which plywood formers and wooden stringers are fitted, the whole being fabric covered except for the aluminium front panels. Roth wings have solid spruce spars to which are fitted wooden ribs, each wing panel being internally and externally wire braced and fabric covered. The wings are set at 6 degrees sweep back at the quarter chord line, Frise type ailerons are fitted only to the lower wings, which have 3 degrees dihedral. Single faired interplane struts and N type cabane struts are fitted. The wing airfoil section is an M6.The main undercarriage is made up of welded steel tube and utilises rubber cord shock absorption. The tail wheel is steerable. A 16 Imperial gallon fuel tank is located immediately aft of the firewall. Engines of from 100-200 h.p. may be fitted.

The 1960 S1-C or Flatwing incorporated a semi-symmetrical airfoil and lower-wing ailerons with a Continental O-200 engine. The first S1-C was Pat Ledford’s (N8L) and the plans were drawn up as it was constructed. They were redrawn in the ’90s by Steen Aero Lab, incorporating many minor changes, one of which was the inclusion of the slightly-longer S1-S fuselage.

Christen-Pitts S1-C N3507

The S-1D is a four aileron version with a modified M-6 airfoil, completely certified. Kits and plans were marketed to home-builders.

The S1-E is an experimental, home-built version of the S1-S, with some crossover in names and parts provided by the factory between the -S and –E. An unknown number of S1-E became certified S1-S.

The S-1S model was first year built in 1974. The price in 1982 was $41,690 as a complete kit, or certified under FAA A8SO.

Christen-Pitts S1-S N55BT

S1-S / Roundwing of 1973 was an S1-D with two different symmetrical airfoils on the upper and lower wings with four ailerons.

S1-S production continued until 1981, when its plans were released for home-builders. Any home-built S1-S predating 1981 was not a true S1-Ss.

S1-SS or Super Stinker Pitts Special used an airfoil and aileron setup derived from the S-1-11/-11B “Super Stinker” aircraft, which was not a Pitts Special nor was it an S1, but a new design meant for world championship aerobatic competition. S1-SS was offered by Steen Aero Lab since the ’90s as supplemental wing plans to fit onto any S1 fuselage.

Christen-Pitts S1-SS N519DC

The 1981 S-1T is a single-seater model which claims roll rates of up to 240 degrees/second. A certified version that superseded the S1-S, with a 200hp engine, constant-speed prop, and new aileron design. Pitts has sold more than 2500 sets of plans for the popular S-1T.

Christen-Pitts S1-T

By 1998 the Pitts S-1 was marketed by Aviat Aircraft.

Gallery

S1 Special
1945
Engine: 55hp Lycoming
Wingspan: 20’0″
Length: 18’3″
Seats: 1

S-1C
Engine: Lycoming IO-360-B4A, 180 hp
Speed max: 147 mph
Cruise: 143 mph
Range: 250 sm
Stall: 64 mph
ROC: 2600 fpm
Take-off dist: 300 ft
Landing dist: 600 ft
HP range: 125-200
Fuel cap: 20 USG
Weight empty: 720 lb
Gross: 1150 lb
Height: 6.25 ft
Length: 15.5 ft
Wing span: 17.33 ft
Wing area: 98 sq.ft
Seats: 1
Landing gear: tail wheel

Engine: Lycoming O-320, 150 hp
Cruise: 150 mph
ROC: 2650 fpm
Range: 300 sm
Span: 17 ft 5 in
Length: 15 ft 6 in
Empty wt: 720 lb
Max wt: 1050 lb

S-1C
Engine: 1 × Textron Lycoming AEIO-540-D4A5, 260 hp (194 kW)
Wingspan: 17 ft 4 in (5.28 m)
Length: 18 ft 9 in (5.71 m)
Maximum speed: 210 mph (338 kph)
Maximum range: 319 miles (513 km)
Service Ceiling: 21,000 ft (6,400 m)

S1-D
Enine: 180hp Lycoming IO-360B
Wingspan: 17’5″
Length: 15’6″
Useful load: 425 lb
Max speed: 145 mph
Cruise speed: 135 mph
Stall: 64 mph
Range: 230 mi
Ceiling: 22,000′

S-1S
First built: 1973
Engine: Lycoming AEIO-360-B4A, 180 hp
TBO: 2000 hr
Prop: Sensenich 2-blade, 72-in
Seats: 1
Length: 15.5 ft
Height: 6.3 ft
Wingspan: 17.3 ft
Wing area: 98.5 sq.ft
Maximum ramp weight: 1150 lb
Maximum takeoff weight: 1150 lb
Standard empty weight: 740 lb
Maximum useful load: 410 lb
Maximum landing weight: 1150 lb
Wing loading: 11.7 lbs/sq.ft
Power loading: 6.4 lbs/hp
Maximum usable fuel: 120 lb
Best rate of climb: 2500 fpm
Service ceiling: 18,000 ft
Maximum speed: 139 kt
75% cruise: 123 kt
55% cruise: 115 kt
Stalling speed: 56 kt
Turbulent-air penetration speed: 134 kt
Fixed tail wheel under carriage
Payload max fuel: 257 lb
Range max fuel/75% pwr: 148 nm/1.2 hr
Range max fuel / 55% pwr: 190 nm/ 1.7 hr
Min field length: 800 ft
Fuel cap: 114 lb

S-IT
Gross Wt. 1150 lb
Empty Wt. 830 lb
Fuel capacity 20 USG
Wing span 17’4”
Length 15’6”
Engine 200-hp AEIO-360-AE1
Top speed 185 mph
Cruise 175 mph
Stall 64 mph
Climb rate 2800 fpm

Aviat Aircraft Pitts S-1
Engine: Lycoming
Wing span: 5.27 m
Wing area: 9.06 sq.m
MAUW: 522 kg
Empty weight: 345 kg
Fuel capacity: 72 lt
Max speed: 222 kph
Cruise speed: 195 kph
Minimum speed: 100 kph
Climb rate: 12.5 m/s
Seats: 1
Fuel consumption: 35 lt/hr
Plan price (1998): US$250

Pitts

Curtiss Pitts
Pitts Aviation
Pitts Aerobatics

1945: Curtis Pitts, Jacksonville FL.
1945: Pitts Aero Service, Gainesville FL.
1955: Homestead FL.
1967: Pitts Aviation, Homestead.
1969: Pitts Aviation Enterprises, Afton WY.
Pitts Aviation Enterprises founded at Florida to market plans for the Curtis Pitts biplane.

New company formed as Pitts Aerobatics in 1977 at Afton, Wyoming, to continue sales and engineering of the Pitts aerobatic biplane at the same location by Aerotek Inc, which formerly built the Pitts S-2 for Pitts Aviation Enterprises.
c.1980: Pitts Aerobatics (pres: E H Anderson)
Aerotek continued to produce the S-2 for Pitts Aerobatics and the single-seat Pitts S-15 for pilots who did not wish to build their own.