| 21. | This equation indicates that a ?v of n times the exhaust velocity requires a mass ratio of e ^ n.
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| 22. | These values are used in equations similar to the rocket equation and are analogous to specific impulse or exhaust velocity.
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| 23. | Rocket engines have extremely high exhaust velocity and thus are best suited for high speeds ( hypersonic ) and great altitudes.
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| 24. | However, the effective exhaust velocity allows for various losses, and notably, is reduced when operated within an atmosphere.
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| 25. | For these drives, at the highest exhaust speeds, energetic efficiency and thrust are all inversely proportional to exhaust velocity.
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| 26. | Where P is the power, F is the thrust and v _ \ text { e } the exhaust velocity.
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| 27. | The attainment of high exhaust velocity or specific impulse ( " I " sp ) is the first concern.
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| 28. | The exhaust velocity of the ions when expelled by the ramjet was assumed not to exceed 100, 000 m / s.
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| 29. | Larger ratio nozzles are more massive but are able to extract more heat from the combustion gases, increasing the exhaust velocity.
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| 30. | For air-breathing engines the effective exhaust velocity is not physically meaningful, although it can be used for comparison purposes nevertheless.
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