Difference between revisions of "Template:VT"
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(!didn't respect thinner atmosphere at higher altitudes;) |
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--> ({{{alt}}} + {{BodyData/Radius|{{{planet}}}}} <!-- | --> ({{{alt}}} + {{BodyData/Radius|{{{planet}}}}} <!-- | ||
--> )^2 * <!-- | --> )^2 * <!-- | ||
| − | --> ( {{BodyData/Pressure|{{{planet}}}}} <!-- | + | --> ( {{BodyData/Pressure|{{{planet}}}}} * e^(-{{{alt}}}/{{BodyData/ScaleHeight|{{{planet}}}}}) <!-- |
--> ) * (1.2230948554874 * 0.008) * 0.2 * 1 <!-- | --> ) * (1.2230948554874 * 0.008) * 0.2 * 1 <!-- | ||
--> ) <!-- | --> ) <!-- | ||
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This template calculates terminal velocity of an object given the planet and the altitude from the planet's surface. It assumes that the coefficient of drag is 0.2 and that the cross-sectional area is 1 m<sup>2</sup>. It also assumes that atmospheric density is equal to the atmospheric pressure multiplied by 1.2230948554874 * 0.008.<ref>See the [[Atmosphere]] article.</ref> | This template calculates terminal velocity of an object given the planet and the altitude from the planet's surface. It assumes that the coefficient of drag is 0.2 and that the cross-sectional area is 1 m<sup>2</sup>. It also assumes that atmospheric density is equal to the atmospheric pressure multiplied by 1.2230948554874 * 0.008.<ref>See the [[Atmosphere]] article.</ref> | ||
| − | Result = ((2·G·M)/((alt+r)<sup>2</sup>·p<sub>0</sub>·1.2230948554874·0.008·0.2·1 m<sup>2</sup>))<sup>½</sup> | + | Result = ((2·G·M)/((alt+r)<sup>2</sup>·p<sub>0</sub>·e<sup>-alt/scale</sup>·1.2230948554874·0.008·0.2·1 m<sup>2</sup>))<sup>½</sup> |
| − | <small>(M is Mass, r is | + | <small>([[Template:BodyData/Mass|M]] is Mass, [[Template:BodyData/Radius|r]] is Radius, [[Template:BodyData/Pressure|p<sub>0</sub>]] is pressure at 0 m altitude (“sea level”) and [[Template:BodyData/ScaleHeight|scale]] is the scale height)</small> |
== Notes == | == Notes == | ||
Revision as of 08:22, 27 March 2013
| Usage | Produces |
|---|---|
{{VT | planet = Kerbin | alt = 0}} |
100.1288989294 |
This template calculates terminal velocity of an object given the planet and the altitude from the planet's surface. It assumes that the coefficient of drag is 0.2 and that the cross-sectional area is 1 m2. It also assumes that atmospheric density is equal to the atmospheric pressure multiplied by 1.2230948554874 * 0.008.[1]
Result = ((2·G·M)/((alt+r)2·p0·e-alt/scale·1.2230948554874·0.008·0.2·1 m2))½
(M is Mass, r is Radius, p0 is pressure at 0 m altitude (“sea level”) and scale is the scale height)
Notes
- ↑ See the Atmosphere article.
