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<!-- This article is a part of [[Wikipedia:WikiProject Aircraft]]. Please see [[Wikipedia:WikiProject Aircraft/page content]] for recommended layout. --> |
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{|{{Infobox |
{|{{Infobox aircraft begin |
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|name =RWD 23 |
|name =RWD 23 |
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|image =RWD 23 - Low wing trainer - SP-BPO - 1939.jpg |
|image =RWD 23 - Low wing trainer - SP-BPO - 1939.jpg |
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|caption = |
|caption = |
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}}{{Infobox |
}}{{Infobox aircraft type |
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|type =Trainer |
|type =Trainer |
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|manufacturer =[[RWD (aircraft manufacturer)|DWL]] |
|manufacturer =[[RWD (aircraft manufacturer)|DWL]] |
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The '''RWD 23''' was a |
The '''RWD 23''' was a Polish low-wing [[trainer aircraft]] of 1938, constructed by the [[RWD (aircraft manufacturer)|RWD]] team, that remained a prototype. |
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==Development== |
==Development== |
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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 [[Flap (aircraft)|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. |
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 [[Flap (aircraft)|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. |
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{{convert|62|hp|abbr=on}} [[Walter Mikron]] II inline engine in front, with two-blade wooden propeller. {{convert|90|hp|abbr=on}} [[Cirrus Minor (engine)|Cirrus Minor]] or 63 hp [[Avia 3]] engines could also to be installed. Fuel tank 45 |
{{convert|62|hp|abbr=on}} [[Walter Mikron]] II inline engine in front, with two-blade wooden propeller. {{convert|90|hp|abbr=on}} [[Cirrus Minor (engine)|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. |
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( |
( |
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==Specifications (RWD 23 prototype) == |
==Specifications (RWD 23 prototype) == |
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{{Aircraft specs |
{{Aircraft specs |
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|ref=Polish Aircraft 1893-1939<ref name="Cynk">{{cite book|last=Cynk|first=Jerzy B.|title=Polish Aircraft 1893-1939|publisher=Putnam & Company Ltd.|location=London|year=1970|edition=1st|pages=572–574}}</ref><!-- reference --> |
|ref=''Polish Aircraft 1893-1939'' <ref name="Cynk">{{cite book|last=Cynk|first=Jerzy B.|title=Polish Aircraft 1893-1939|publisher=Putnam & Company Ltd.|location=London|year=1970|edition=1st|pages=572–574}}</ref><!-- reference --> |
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|prime units?=met<!-- imp or kts first for US aircraft, and UK aircraft pre-metrification, |
|prime units?=met<!-- imp or kts first for US aircraft, and UK aircraft pre-metrification, |
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met(ric) first for all others. You MUST choose a format, or no specifications will show --> |
met(ric) first for all others. You MUST choose a format, or no specifications will show --> |
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|lower span in= |
|lower span in= |
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|lower span note= |
|lower span note= |
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|swept m=<!-- swing-wings --> |
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|swept ft=<!-- swing-wings --> |
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|swept in=<!-- swing-wings --> |
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|swept note= |
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|dia m=<!-- airships etc --> |
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|dia ft=<!-- airships etc --> |
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|dia in=<!-- airships etc --> |
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|width m=<!-- if applicable --> |
|width m=<!-- if applicable --> |
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|width ft=<!-- if applicable --> |
|width ft=<!-- if applicable --> |
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|wing area sqft= |
|wing area sqft= |
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|wing area note= |
|wing area note= |
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|swept area sqm=<!-- swing-wings --> |
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|swept area sqft=<!-- swing-wings --> |
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|swept area note= |
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|volume m3=<!-- lighter-than-air --> |
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|volume ft3=<!-- lighter-than-air --> |
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|volume note= |
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|aspect ratio=<!-- sailplanes --> |
|aspect ratio=<!-- sailplanes --> |
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|airfoil= |
|airfoil= |
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|max takeoff weight lb= |
|max takeoff weight lb= |
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|max takeoff weight note= |
|max takeoff weight note= |
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|fuel capacity={{convert|50| |
|fuel capacity={{convert|50|L|impgal|abbr=on|0}} |
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|lift kg=<!-- lighter-than-air --> |
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|lift lb=<!-- lighter-than-air --> |
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|lift note= |
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|more general= |
|more general= |
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<!-- |
<!-- |
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|eng1 hp=65<!-- prop engines --> |
|eng1 hp=65<!-- prop engines --> |
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|eng1 shp=<!-- prop engines --> |
|eng1 shp=<!-- prop engines --> |
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|eng1 kn=<!-- jet/rocket engines --> |
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|eng1 lbf=<!-- jet/rocket engines --> |
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|eng1 note=<br/> |
|eng1 note=<br/> |
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**or 1 x {{convert| |
**or 1 x {{convert|48|kW|hp|abbr=on}} [[Avia 3]] |
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**or 1 x {{convert|67 |
**or 1 x {{convert|67|kW|hp|abbr=on}} [[Blackburn Cirrus Minor]] |
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|power original= |
|power original= |
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|thrust original= |
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|eng1 kn-ab=<!-- afterburners --> |
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|eng1 lbf-ab=<!-- afterburners --> |
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|eng2 number= |
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|eng2 name= |
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|eng2 type= |
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|eng2 kw=<!-- prop engines --> |
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|eng2 hp=<!-- prop engines --> |
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|eng2 shp=<!-- prop engines --> |
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|eng2 kn=<!-- jet/rocket engines --> |
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|eng2 lbf=<!-- jet/rocket engines --> |
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|eng2 note= |
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|eng2 kn-ab=<!-- afterburners --> |
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|eng2 lbf-ab=<!-- afterburners --> |
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|eng3 number= |
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|eng3 name= |
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|eng3 type= |
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|eng3 kw=<!-- prop engines --> |
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|eng3 hp=<!-- prop engines --> |
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|eng3 shp=<!-- prop engines --> |
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|eng3 kn=<!-- jet/rocket engines --> |
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|eng3 lbf=<!-- jet/rocket engines --> |
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|eng3 note= |
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|eng3 kn-ab=<!-- afterburners --> |
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|eng3 lbf-ab=<!-- afterburners --> |
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|more power= |
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|prop blade number=<!-- propeller aircraft --> |
|prop blade number=<!-- propeller aircraft --> |
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|prop name= |
|prop name= |
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|prop dia in=<!-- propeller aircraft --> |
|prop dia in=<!-- propeller aircraft --> |
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|prop dia note= |
|prop dia note= |
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|rot number=<!-- helicopters --> |
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|rot dia m=<!-- helicopters --> |
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|rot dia ft=<!-- helicopters --> |
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|rot dia in=<!-- helicopters --> |
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|rot area sqm=<!-- helicopters --> |
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|rot area sqft=<!-- helicopters --> |
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|rot area note= |
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<!-- |
<!-- |
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Performance |
Performance |
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|never exceed speed kts= |
|never exceed speed kts= |
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|never exceed speed note= |
|never exceed speed note= |
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|minimum control speed kmh= |
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|minimum control speed mph= |
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|minimum control speed kts= |
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|minimum control speed note= |
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|range km=450 |
|range km=450 |
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|range miles= |
|range miles= |
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|roll rate=<!-- aerobatic --> |
|roll rate=<!-- aerobatic --> |
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|glide ratio=<!-- sailplanes --> |
|glide ratio=<!-- sailplanes --> |
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|climb rate ms=2 |
|climb rate ms=2 |
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|climb rate ftmin= |
|climb rate ftmin= |
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|climb rate note= |
|climb rate note= |
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|time to altitude={{convert|1,000|m|ft|abbr=on |
|time to altitude={{convert|1,000|m|ft|abbr=on}} in 8 minutes |
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|sink rate ms=<!-- sailplanes --> |
|sink rate ms=<!-- sailplanes --> |
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|sink rate ftmin=<!-- sailplanes --> |
|sink rate ftmin=<!-- sailplanes --> |
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Latest revision as of 11:26, 26 December 2023
| RWD 23 | |
|---|---|
| |
| Role | Trainer |
| Manufacturer | DWL |
| Designer | RWD team |
| First flight | 1938/1939 |
| Status | prototype |
| Primary user | Poland |
| Number built | 1 |
The RWD 23 was a Polish low-wing trainer aircraft of 1938, constructed by the RWD team, that remained a prototype.
Development[edit]
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.[1] 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[edit]
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 (46 kW) Walter Mikron II inline engine in front, with two-blade wooden propeller. 90 hp (67 kW) 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)[edit]
Data from Polish Aircraft 1893-1939 [2]
General characteristics
- Crew: 2
- Length: 8 m (26 ft 3 in)
- Wingspan: 11.1 m (36 ft 5 in)
- Mid wingspan: 1.9 m (6 ft 3 in)
- Wing area: 16 m2 (170 sq ft)
- Empty weight: 325 kg (717 lb)
- Gross weight: 550 kg (1,213 lb)
- Fuel capacity: 50 L (11 imp gal)
- Powerplant: 1 × Walter Mikron II 4-cylinder air-cooled inverted in-line piston engine, 48 kW (65 hp)
- or 1 x 48 kW (64 hp) Avia 3
- or 1 x 67 kW (90 hp) Blackburn Cirrus Minor
Performance
- Maximum speed: 171 km/h (106 mph, 92 kn) at sea level
- Cruise speed: 145 km/h (90 mph, 78 kn)
- Stall speed: 65 km/h (40 mph, 35 kn)
- Range: 450 km (280 mi, 240 nmi)
- Service ceiling: 4,000 m (13,000 ft)
- Rate of climb: 2 m/s (390 ft/min)
- Time to altitude: 1,000 m (3,300 ft) in 8 minutes
- Wing loading: 34.4 kg/m2 (7.0 lb/sq ft)
- Power/mass: 0.081 kW/kg (0.049 hp/lb)
See also[edit]
Aircraft of comparable role, configuration, and era
References[edit]
- ^ Andrzej Glass (2003). Słownik biograficzny techników polskich, SBTP: Warsaw, p. 24: fragment of its entry about Tadeusz Chyliński: (Polish: W 1937 r. podjął prace w Doświadczalnych Warsztatach Lotniczych (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. PW.)
- ^ Cynk, Jerzy B. (1970). Polish Aircraft 1893-1939 (1st ed.). London: Putnam & Company Ltd. pp. 572–574.
- Andrzej Glass: "Polskie konstrukcje lotnicze 1893-1939" (Polish aviation constructions 1893-1939), WKiŁ, Warsaw 1977 (in Polish), no ISBN
External links[edit]
Wikimedia Commons has media related to RWD 23.