1934 bomber-reconnaissance aircraft family by PZL
The PZL.23 "Karaś" ("crucian carp") was a Polish light bomber and reconnaissance aircraft designed in the mid-1930s by PZL in Warsaw.
During the interwar period, the Polish High Command had placed considerable emphasis upon the role of armed aerial reconnaissance aircraft. To meet this interest, during 1931, PZL decided to embark on the development of a new combat aircraft to meet this role. An earlier proposal for a fast single-engine passenger airliner, designated the "PZL.13", was adopted as the basis of the new design. The new aircraft, which was designated as the PZL.23, a relatively modern design, which integrated features such as an all-metal body and unconventional wing construction. As the British Bristol Pegasus radial engine was licensed for use in Poland only, export aircraft were instead equipped with the Gnome-Rhône 14N engine. Powered as such and along with some airframe changes, the PZL.23 became the PZL.43.
It was the primary Polish reconnaissance bomber in use during the invasion of Poland. On 2 September 1939, a single PZL.23B of the 21st Escadrille was responsible for the bombing of a factory in Ohlau, inside Germany; the attack represented the first bombing raid to be conducted against a target in territory within the Third Reich. During the following days, the PZL.23 bomber escadrilles were deployed to attack several advancing German armoured columns; they often conducted these attacks at low altitudes, which made them vulnerable to anti-aircraft fire. By the end of 1939, around 120 PZL.23s (86 per cent of the Polish Air Force's inventory of the type) were destroyed; however, of these, only 67 had been lost as a direct result of enemy actions.
Development.
Background.
As a result of wartime experiences acquired by the Polish armed forces during the 1919-1921 Polish–Soviet War, during the 1920s and 1930s (now known as the interwar period), a great emphasis was placed upon the role of armed aerial reconnaissance aircraft. According to aviation historian J. B. Cynk, the role was recognised by the Polish High Command as being, aside from the basic fighter aircraft, the most important type of aerial unit in their doctrine. As such, considerable resources and effort was placed upon the creation of sizable army cooperation escadrilles, which were initially principally equipped with foreign-built biplanes such as the French Breguet 19 and Potez 25.
During the late 1920s, it had become increasingly obvious that the existing types used for the aerial reconnaissance role would need to be replaced, which led to the Ministry of War's Aviation Department defining a set of a broad performance requirements desired in an aircraft to fulfil the role. Around the same time, at the Polish state-owned aviation works PZL, the aircraft designer Stanisław Prauss had been studying options for a new fast single-engine airliner, to be designated the "PZL.13". An advanced low-wing cantilever monoplane design proposal with an all-metal structure and a Pratt &amp; Whitney Wasp radial engine was selected for further development, however during early 1931, the Ministry of Transport cancelled the project and terminated its sponsorship amid a lack of interest. Accordingly, PZL were keen to embark upon a replacement project in the place of the PZL.13 venture. Following a series of consultations between the company and the Aviation Department, it was decided to embark upon the design of a three-man armed reconnaissance-bomber, using the abortive PZL.13 passenger transport airliner as a starting point for the new aircraft. The resulting design, designated the "PZL.23", was only one of several proposals to be produced; alternatives included the "PWS.19", a high-wing monoplane, and the Lublin R.XVII, a clean twin-seat biplane with a retractable undercarriage. During late 1931, the Aviation Department decided to opt for the PZL submission.
Design phase.
During early 1932, PZL were authorised to formally proceed with preliminary design work on what would become the PZL.23. An early key design decision was the selection of the British Bristol Pegasus radial engine to power the type, which was domestically produced by Skoda in their Warsaw plant. The emerging design was for a modern combat aircraft, integrating features such as an all-metal body and unconventional wing construction, being built around light closed profiles instead of spars (this wing design had been previously introduced on the PZL.19).
During the spring of 1932, the preliminary design was approved in principle by the Aviation Department, however, in accordance with the department's expressed preferences, the ventral gun turret was redesigned for increased field of fire, as well as to accommodate more capable bomb-aiming equipment. During late 1932, authorisation to proceed with the construction of a batch of three prototypes along with one static-test airframe. However, development would not prove to be a straightforward venture. The diverse requirements of the PZL.23 imposed considerable hurdles in the design phase; in order to produce a relatively fast aircraft, a heavy airframe was practically necessitated, however, it was also important for the type to be able to operate from constrained austere airstrips rapidly established on the front lines of warzones; producing a suitable compromise was not easy.
The venture has been considered to be pioneering in some aspects of its design, which contributed to its design complications. Static testing by the Institute of Aviation Technical Research (ITBL) was both protracted and determined some components to process insufficient strength; these were not completed until 1933. However, completion of the prototypes was delayed to incorporate modifications to address the findings. The name "Karaś" was selected for the type around this time.
Into flight.
On 1 April 1934, the "P.23/I" first prototype conducted its maiden flight; it was quickly followed by the second "P.23/II" prototype. Early flight testing revealed several issues that needed to be resolved, including tail flutter and vibration in the rear fuselage area; another difficulty identified even prior to the first flight was the inadequate visibility from the cockpit for both the pilot and observer. Various measures to rectify these issues were incorporated onto the second and third prototypes.
During the following year, the third "P.23/III" prototype was completed; on this aircraft, various further refinements were included, such as the pilot's seat having been raised into a new fully glazed canopy arrangement and the engine being positioned lowered down, giving the aircraft a characteristic hump-nose, as to improve the pilot's external field of vision. The fuselage bomb bay of the earlier prototype was eliminated; instead, the entire payload was carried externally on racks fixed onto the underside of the wing's center-section. Various other alterations were made to the wings, including the adoption of more effective slotted ailerons, improved flaps and center-section slots, the latter feature served to smooth the airflow over the tail when flown at high angles of incidence.
During mid-1935, the second prototype was lost in a crash shortly after a take-off conducted at the maximum loading weight, killing the crew on board. The remaining airworthiness tests and service acceptance trials were completed successfully using the third prototype. Further refinements had been incorporated into the third prototype during the test programme to eventually conform with the standards of subsequent production-standard aircraft. Amongst the final changes were the adoption of a Pegasus VIII engine, after which it was used as the development aircraft for the "PZL.23B" variant of the type.
As a consequence of its favourable flight test programme, the aircraft was approved to enter full-scale production during the second half of 1935. The first series, which was given the designation of "PZL.23A", was fitted with a single Bristol Pegasus IIM2 engine, which possessed an upper thrust capability of 670 hp (500 kW) thrust. Early on, the limited availability of the Pegasus engine led to production delays. However, since this engine proved to be unreliable during testing, the final variant, which was designated "PZL.23B", was fitted with the newer Pegasus VIII model, which was capable of generating a maximum of 720 hp (537 kW) of thrust.
Further development.
The Bristol engines were licensed for use in Poland only, so for export purposes the Gnome-Rhône engines were used in a variety of PZL designs. A development of the PZL.23 was the PZL.43 light bomber powered by a Gnome-Rhône 14N engine, with significant changes in the fuselage structure compared to its predecessor. The final export variant to be developed was "PZL.43A"; it was furnished with a single 1,020 hp Gnome-Rhône 14N-01 engine. 52 PZL.43s were made in total, all for Bulgaria only. The new engine improved the aircraft's performance considerably, resulting in the maximum speed being increased to 365 km/h.
During 1936, 40 PZL.23As were produced. Between late 1936 and February 1938, 210 PZL.23Bs were produced with the new engines. They were also known as Karaś A and B or Karaś I and II. All PZL.23s had military numbers from 44.1 to 44.250.Sometimes the aircraft is called the "PZL P.23", but despite an abbreviation P.23 painted on a tail fin, the letter "P" was generally reserved for fighters of Pulawski's design (like PZL P.11). In November 1936, one aircraft was shown at the Paris Air Show, where it was met with interest.
During this period, PZL developed the PZL.46 Sum, a new light bomber, which was partly based on the PZL.23 design. However, only a pair of prototypes were completed during 1938. There was also a single experimental version designated as "PZL.42." This version featured a double tail fin configuration and a modified bombardier gondola which was retractable into the fuselage.
Design.
The PZL.23 Karaś was a low-wing cantilever monoplane, featuring all-metal, metal-covered construction. The crew of three consisted of a pilot, a bombardier, and a rear gunner. The bombardier's combat station was situated in a gondola underneath the hull, where he could also operate an underbelly machine gun. The pilot was positioned within a fully enclosed air-conditioned and heated cockpit, while the observer was seated directly behind him and could descend into the ventral gondola during applicable parts of a given mission. The fixed undercarriage comprised a pair of cantilever struts and single tail skid, all of which were outfitted with pneumatic shock absorbers built by Czechoslovakian company Avia. When prepared for operating from rough or austere airfields, the streamlined fairings over the wheels would have to be removed in advance.
The aircraft were equipped with one of the following engines: Bristol Pegasus IIM2 normal: 570 hp (425 kW), maximum: 670 hp (500 kW) - PZL.23A; Pegasus VIII normal: 650 hp (485 kW), maximum: 720 (537 kW) - PZL.23B. Early Polish-built engines had encountered several common issues, including crankshaft fractures and reduction gears jamming; the original engine manufacturer, Bristol, had not amended the drawings and specifications provided to Poland to incorporate their latest improvements to the Pegasus, which addressed these issues. For the export market, it was outfitted with either the Gnome-Rhône 14K or Gnome-Rhône 14N-01 engines. Regardless of the engine adopted, the aircraft was always outfitted with a two-blade propeller.
One of the more unusual features of the PZL.23 was the design of its three-piece low-mounted wing. In order to produce a wing that was both light and strong, Prauss had opted to use a relatively new wing structure which had been recently designed by Polish engineer Fraciszek Misztal. This wing combined a revolutionary heavy-gauge corrugated duralumin center box and a multi-cellular trailing edge, along with a partially stressed exterior skin composed of duralumin; according to Cynk, it was one of the earliest implementations of a metal sandwich structure in the field of aviation.
The fuselage of the PZL.23 had an oval-section structure, composed of a mixture of duralumin frames and stringers, which were strengthened via several struts on the middle section. The exterior of the fuselage was covered with smooth duralumin sheet, which was internally reinforced in some areas by corrugated sheeting. The rear fuselage featured a semi-monocoque structure. A cantilever structure composed of ribs and spars was used for the tail unit; the fin and tailplane were covered by duralumin sheeting, while the rudder and elevators had finely corrugated exterior surfaces.
The aircraft's offensive payload consisted of bombs. These were carried underneath the wings using racks; the maximum load was (6 x 100 kg and 2 x 50 kg). While plans to incorporate the Swiatecki bomb-release gear had been mooted, however, they were eliminated from the design during the prototype stage due to disagreements between the Aviation Department and the inventor regarding the manufacturing arrangements. The PZL.23 was also armed with several machine guns, including a defensive ventral gun turret; additional positions, such as a twin-gun mounting on the upper fuselage were considered but never pursued. A typical gun armament included either one or a