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131:. Specific impulse and effective exhaust velocity are dependent on the nozzle design unlike the characteristic velocity, explaining why C-star is an important value when comparing different propulsion system efficiencies. c* can be useful when comparing actual combustion performance to theoretical performance in order to determine how completely chemical energy release occurred. This is known as
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512:{\displaystyle c^{*}={\frac {I_{sp}g_{0}}{C_{F}}}={\frac {c}{C_{F}}}={\sqrt {{\frac {RT_{c}}{\gamma }}{\Bigl (}{\frac {\gamma +1}{2}}{\Bigr )}^{\frac {\gamma +1}{\gamma -1}}}}}
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This article is about rocketry. For the algebraic structure in mathematics, see
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80:, which is the effective exhaust velocity related to the
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is the gravitational acceleration at sea-level (m/s)
201:{\displaystyle c^{*}={\frac {p_{c}A_{t}}{\dot {m}}}}
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735:9th Edition by George P. Sutton, Oscar Biblarz
729:7th Edition by George P. Sutton, Oscar Biblarz
68:performance, and is used to compare different
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237:is the characteristic velocity (m/s, ft/s)
124:{\displaystyle I_{s}={\frac {c}{g_{0}}}}
632:is the effective exhaust velocity (m/s)
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76:. c* should not be confused with
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56:, or C-star is a measure of the
713:is the chamber temperature (K)
1:
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16:Measure of rocket performance
755:. You can help Knowledge by
338:of the engine (kg/s, slug/s)
7:
751:This rocketry article is a
733:Rocket Propulsion Elements,
727:Rocket Propulsion Elements,
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327:{\displaystyle {\dot {m}}}
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610:is the thrust coefficient
684:per unit weight (J/kg-K)
647:{\displaystyle \gamma }
27:Characteristic velocity
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812:Aerospace engineering
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706:{\displaystyle T_{c}}
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658:for the exhaust gases
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603:{\displaystyle C_{F}}
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574:{\displaystyle g_{0}}
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541:{\displaystyle I_{s}}
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303:of the throat (m, in)
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292:{\displaystyle A_{t}}
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656:specific heat ratio
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74:propulsion systems
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807:Rocket propulsion
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673:{\displaystyle R}
625:{\displaystyle c}
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60:performance of a
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82:specific impulse
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133:c*-efficiency
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757:expanding it
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70:propellants
796:Categories
721:References
58:combustion
21:C* algebra
642:γ
498:−
495:γ
484:γ
458:γ
443:γ
354:∗
319:˙
270:(Pa, psi)
223:∗
192:˙
155:∗
42:∗
802:Rocketry
268:pressure
680:is the
654:is the
548:is the
334:is the
299:is the
139:Formula
66:nozzle
753:stub
301:area
84:by:
72:and
552:(s)
29:or
798::
135:.
784:e
777:t
770:v
759:.
699:c
695:T
668:R
620:c
596:F
592:C
567:0
563:g
534:s
530:I
501:1
490:1
487:+
476:)
468:2
464:1
461:+
450:(
437:c
433:T
429:R
421:=
414:F
410:C
406:c
401:=
394:F
390:C
383:0
379:g
373:p
370:s
366:I
359:=
350:c
316:m
285:t
281:A
252:c
248:p
219:c
189:m
181:t
177:A
171:c
167:p
160:=
151:c
115:0
111:g
107:c
102:=
97:s
93:I
78:c
38:c
23:.
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