jsbsim.js
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JSBSim flight dynamics model ported to JavaScript
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text/xml
<!--
File: WrightGR-2600.xml
Author: Aero-Matic v 0.7
Date: 14 March 2010
Version 1.02
Inputs:
name: WrightGR-2600
type: piston
power: 1600.0 hp
augmented? no
injected? no
References :
==========
- http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet
(FAA certificate, TC704 - 25 january 1939, B-314) :
Engine limits : * maximum except take-off (straight line manifold pressure variation) : 33.2 in. hg. 2100 rpm (1200 hp)
at 5400 ft, 35.0 in. hg. 2100 rpm (1200 hp) at sea level.
* take-off (2 minutes), 42.5 in. hg. 2400 rpm (1550 hp).
- http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet
(FAA certificate, TC704 - 2 may 1941 B-314A) :
Engine limits : * maximum except take-off (straight line manifold pressure variation) : 35.8 in. hg. 2300 rpm (1350 hp)
at 6200 ft, 37.5 in. hg. 2300 rpm (1350 hp) at sea level.
* take-off (2 minutes), 43.5 in. hg. 2400 rpm (1600 hp).
- http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet
(FAA certificate, TC176 - Wright Double row Cyclone GR-260025) :
Displacement : 2603 cu. in.
Bore : 6.125 in.
Stroke : 6.312 in.
Compression : 6.85.
-->
<!-- this is an engine of B-314 A. -->
<piston_engine name="Wright Double Row Cyclone GR-2600 709C14AC1">
<!-- Range is adjusted to the economic cruise, by volumetric efficiency :
- in the FAA certificate the fuel capacity of 314A is 5688 gallons where 1 gallon = 6 lb !
- the economic cruise speed is 110 kt indicated, or 130 kt true (KSFO - PHNL 2080 NM / 16 h),
that is a range of 34.75 h = 5200 miles / 130 kt,
or 5688 US gal / 34.75 h = 164 gallons/h for all engines, or 41 gallons/h per engine.
The 314A (314) was unable to reach 5200 (3500) miles at the cruise speed of 160 kt.
To be above atmospheric pressure :
- 10 PSI for 43.5 inhg max at 2400 RPM, sea level : takeoff, full throttle.
- 7 PSI for 37.5 inhg max at 2300 RPM, sea level.
- 6 PSI for 35.8 inhg max at 2300 RPM, 6200 ft.
-->
<minmp unit="INHG"> 10.0 </minmp>
<maxmp unit="INHG"> 43.5 </maxmp> <!-- aeromatic 30.0 -->
<displacement unit="IN3"> 2603.00 </displacement>
<bore unit="IN">6.125</bore>
<stroke unit="IN">6.312</stroke>
<compression-ratio>6.85</compression-ratio>
<volumetric-efficiency>0.6</volumetric-efficiency>
<maxhp> 1600.00 </maxhp>
<cycles> 2.0 </cycles>
<idlerpm> 700.0 </idlerpm>
<maxrpm> 2400.0 </maxrpm>
<maxthrottle> 1.0 </maxthrottle>
<minthrottle> 0.1 </minthrottle>
<sparkfaildrop> 0.0 </sparkfaildrop>
<numboostspeeds> 2 </numboostspeeds>
<boostoverride> 0 </boostoverride>
<takeoffboost> 10 </takeoffboost>
<ratedboost1> 7 </ratedboost1>
<ratedpower1> 1350 </ratedpower1>
<ratedrpm1> 2300 </ratedrpm1>
<ratedaltitude1 > 0 </ratedaltitude1>
<ratedboost1> 6 </ratedboost1>
<ratedpower1> 1350 </ratedpower1>
<ratedrpm1> 2300 </ratedrpm1>
<ratedaltitude1 > 6200 </ratedaltitude1>
</piston_engine>