Svoboda | Graniru | BBC Russia | Golosameriki | Facebook

To install click the Add extension button. That's it.

The source code for the WIKI 2 extension is being checked by specialists of the Mozilla Foundation, Google, and Apple. You could also do it yourself at any point in time.

4,5
Kelly Slayton
Congratulations on this excellent venture… what a great idea!
Alexander Grigorievskiy
I use WIKI 2 every day and almost forgot how the original Wikipedia looks like.
Live Statistics
English Articles
Improved in 24 Hours
Added in 24 Hours
Languages
Recent
Show all languages
What we do. Every page goes through several hundred of perfecting techniques; in live mode. Quite the same Wikipedia. Just better.
.
Leo
Newton
Brights
Milds

Walter Sagitta

From Wikipedia, the free encyclopedia

Sagitta
Type Piston aero engine
National origin Czechoslovakia
Manufacturer Walter Aircraft Engines
First run 1937

The Walter Sagitta was a Czechoslovakian, air-cooled, inverted V-12 engine that first ran in 1937. This was one of several smaller, low-mass medium power pre-war V-12 engines produced. With a displacement of 18.4 liters (1,123 cu in), it produced up to 373 kW (550 hp) at 2,500 rpm.[1]

Variants

Sagitta I-MR
410 kW (550 hp) at 2,500rpm at 2,500 m (8,200 ft) - rated height[2]
Sagitta I-SR
400 kW (535 hp) at 2,500rpm at 3,800 m (12,500 ft) - rated height[2]
Sagitta II R.C.
388 kW (520 hp), fully supercharged.[3]
Alfa Romeo 122
Licensed production.

Applications

Specifications (Sagitta I-MR)

Left side view

Data from Jane's.[2]

General characteristics

  • Type: 12-cylinder inverted vee piston engine
  • Bore: 118 mm (4.65 in)
  • Stroke: 140 mm (5.51 in)
  • Displacement: 18.372 L (1,121.1 cu in)
  • Length: 1,914 mm (75.35 in)
  • Width: 725 mm (28.54 in)
  • Height: 796 mm (31.34 in)
  • Dry weight: 372 kg (820 lb)

Components

  • Valvetrain: Enclosed push-rod operated rockers, two valves per cylinder closed by triple springs
  • Supercharger: 8.7 times crankshaft speed
  • Fuel system: Automatic boost and mixture control by a horizontal carburettor
  • Fuel type: 85 Octane petrol
  • Oil system: Dry sump, one pressure pump and two scavenge pumps
  • Cooling system: Air-cooled

Performance

  • Power output:
    • Take-off: 418 kW (560 hp) at 2,500 rpm
    • Rated power: 410 kW (550 hp) at 2,500 rpm at 2,300 m (7,500 ft)
    • Maximum power: 447 kW (600 hp) at 2,500 rpm at 1,750 m (5,740 ft)
  • Specific power: 24.29 kW/L (0.534 hp/(cu in))
  • Compression ratio: 6.25:1
  • Specific fuel consumption: 0.315 - 0.328 kg/(kW h) (0.525 - 0.548 lb/(hp h))
  • Oil consumption: 0.004 - 0.0067 kg/(kW h) (0.0067 - 0.11 lb/(hp h))
  • Power-to-weight ratio: 1.046 kW/kg (0.636 hp/lb)

See also

Comparable engines

Related lists

References

Notes
  1. ^ Gunston 1989, p. 174.
  2. ^ a b c Jane's All the World's Aircraft 1938. London: Sampson, Low & Martin company Limited. 1938.
  3. ^ Flight - 14 October 1937, p. 381. Retrieved: 8 November 2012
Bibliography
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
This page was last edited on 11 December 2022, at 01:59
Basis of this page is in Wikipedia. Text is available under the CC BY-SA 3.0 Unported License. Non-text media are available under their specified licenses. Wikipedia® is a registered trademark of the Wikimedia Foundation, Inc. WIKI 2 is an independent company and has no affiliation with Wikimedia Foundation.