RWD 23
title: "RWD 23" type: doc version: 1 created: 2026-02-28 author: "Wikipedia contributors" status: active scope: public tags: ["1930s-polish-civil-trainer-aircraft", "rwd-aircraft", "low-wing-aircraft", "single-engined-tractor-aircraft", "aircraft-first-flown-in-1938", "aircraft-with-fixed-conventional-landing-gear"] topic_path: "geography/poland" source: "https://en.wikipedia.org/wiki/RWD_23" license: "CC BY-SA 4.0" wikipedia_page_id: 0 wikipedia_revision_id: 0
::data[format=table title="Infobox aircraft"]
| Field | Value |
|---|---|
| name | RWD 23 |
| image | RWD 23 - Low wing trainer - SP-BPO - 1939.jpg |
| aircraft_type | Trainer |
| manufacturer | DWL |
| designer | RWD team |
| status | prototype |
| primary_user | Poland |
| number_built | 1 |
| first_flight | 1938/1939 |
| :: |
| name = RWD 23 | logo = | logo_size = | image = RWD 23 - Low wing trainer - SP-BPO - 1939.jpg | alt = | caption = | long_caption = | other_names = | aircraft_type = Trainer | aim = | outcome = | related = | national_origin = | manufacturer = DWL | design_group = | designer = RWD team | builder = | issuer = | status = prototype | owners = | primary_user = Poland | more_users = | service = | major_applications = | proposals = | prototypes = | number_built = 1 | construction_number = | civil_registration = | military_serial = | radio_code = | requirement = | aircraft_carried = | flights = | total_hours = | total_distance = | construction_date = | introduction = | retired = | first_flight = 1938/1939 | initiated = | in_service = | last_flight = | expected = | developed_from = | variants = | developed_into = | preservation = | fate = | predecessors = | successors = | concluded = The RWD 23 was a Polish low-wing trainer aircraft of 1938, constructed by the RWD team, that remained a prototype.
Development
The aircraft was designed in 1938 to fill the gap in the Polish trainer aircraft, by creating a light low-wing trainer. All trainers built in series in Poland to that point were high-wing monoplanes, for example the RWD-8 or the various biplanes. The main designer was Andrzej Anczutin of the RWD bureau. Among the designers were also Bronisław Żurakowski and Tadeusz Chyliński. Chyliński designed the base mount for its engine. The plane was similar to de Havilland Moth Minor, but over 100 kg lighter. Low power output and simple wooden construction would make it cheap and economical in service, and therefore it might replace the RWD-8 in aeroclubs.
The first prototype (registration SP-BPO) was flown in late 1938 or early 1939 in Warsaw by E. Przysiecki. It underwent factory trials in June 1939, then it was given to tests to the Aviation Technical Institute. It was destroyed in the first days of World War II, in September 1939. The plane was found as successful, it could also perform basic aerobatics.
The second improved prototype was under construction when the war broke out, but it was not completed. The LOPP paramilitary organization ordered a series of 10 aircraft, that were not completed due to the war.
Description
Wooden construction low-wing cantilever monoplane, conventional in layout, with a fixed landing gear and open cockpits. Fuselage semi-monocoque, rectangular in cross-section, plywood-covered. Single-piece trapezoid wings with rounded tips, single-spar, plywood (front) and canvas covered, fitted with flaps. Conventional tail of a shape typical to RWD designs, like RWD 8, plywood (fins) and canvas (elevators and rudder) covered. Two open cockpits in tandem, with individual windshields and twin controls. Rear cockpit was raised a bit for a better view. Conventional fixed landing gear with a rear skid, main gear in aerodynamic covers.
62 hp Walter Mikron II inline engine in front, with two-blade wooden propeller. 90 hp Cirrus Minor or 63 hp Avia 3 engines could also to be installed. Fuel tank 45 L in a fuselage, cruise fuel consumption 14 L/h. (
Specifications (RWD 23 prototype)
|ref=Polish Aircraft 1893-1939 |prime units?=met met(ric) first for all others. You MUST choose a format, or no specifications will show -- General characteristics
|genhide=
|crew=2 |capacity= |length m=8 |length ft= |length in= |length note= |span m=11.1 |span ft= |span in= |span note= |upper span m= |upper span ft= |upper span in= |upper span note= |mid span m=1.9 |mid span ft= |mid span in= |mid span note= |lower span m= |lower span ft= |lower span in= |lower span note= |width m= |width ft= |width in= |width note= |height m= |height ft= |height in= |height note= |wing area sqm=16 |wing area sqft= |wing area note= |aspect ratio= |airfoil= |empty weight kg=325 |empty weight lb= |empty weight note= |gross weight kg=550 |gross weight lb= |gross weight note= |max takeoff weight kg= |max takeoff weight lb= |max takeoff weight note= |fuel capacity=50 L |more general= Powerplant
|eng1 number=1 |eng1 name=Walter Mikron II |eng1 type= 4-cylinder air-cooled inverted in-line piston engine |eng1 kw= |eng1 hp=65 |eng1 shp= |eng1 note=
- or 1 x 48 kW Avia 3
- or 1 x 67 kW Blackburn Cirrus Minor |power original= |prop blade number= |prop name= |prop dia m= |prop dia ft= |prop dia in= |prop dia note= Performance -- |perfhide=
|max speed kmh=171 |max speed mph= |max speed kts= |max speed note=at sea level |max speed mach= |cruise speed kmh=145 |cruise speed mph= |cruise speed kts= |cruise speed note= |stall speed kmh=65 |stall speed mph= |stall speed kts= |stall speed note= |never exceed speed kmh= |never exceed speed mph= |never exceed speed kts= |never exceed speed note= |range km=450 |range miles= |range nmi= |range note= |combat range km= |combat range miles= |combat range nmi= |combat range note= |ferry range km= |ferry range miles= |ferry range nmi= |ferry range note= |endurance= |ceiling m=4,000 |ceiling ft= |ceiling note= |g limits= |roll rate= |glide ratio= |climb rate ms=2 |climb rate ftmin= |climb rate note= |time to altitude=1,000 m in 8 minutes |sink rate ms= |sink rate ftmin= |sink rate note= |lift to drag= |wing loading kg/m2=34.4 |wing loading lb/sqft= |wing loading note= |disk loading kg/m2= |disk loading lb/sqft= |disk loading note= |fuel consumption kg/km= |fuel consumption lb/mi= |power/mass=0.081 kW/kg (0.049 hp/lb) |thrust/weight=
|more performance= Armament
|armament= specific parameters, remove this parameter-- |guns= |bombs= |rockets= |missiles= |hardpoints= |hardpoint capacity= |hardpoint rockets= |hardpoint missiles= |hardpoint bombs= |hardpoint other=
|avionics=
References
- Andrzej Glass: "Polskie konstrukcje lotnicze 1893-1939" (Polish aviation constructions 1893-1939), WKiŁ, Warsaw 1977 , no ISBN
References
- Andrzej Glass (2003). ''Słownik biograficzny techników polskich'', SBTP: Warsaw, p. 24: fragment of its entry about [[Tadeusz Chyliński]]: ({{langx. pl. W 1937 r. podjął prace w [[Doświadczalne Warsztaty Lotnicze. Doświadczalnych Warsztatach Lotniczych]] ([[RWD (aircraft manufacturer). RWD]]) jako konstr., jednocześnie kontynuowal studia. Pracował przy dok. seryjnej samolotu obserwacyjnego [[RWD-14 Czapla]], następnie zaprojektował plat samolotu zawodniczego [[RWD-19]], kadlub samolotu dyspozycyjnego [[RWD-18]], łoże silnika do samolotu szk. RWD-23 i dźwigar płata samolotu myśliwskiego [[RWD-25]]. W l. 1933-38 byl czl. Sekcji Lotniczej Kola Mechaników Stud. [[Warsaw Technical University. PW]].)
- Cynk, Jerzy B.. (1970). "Polish Aircraft 1893-1939". Putnam & Company Ltd..
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