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Rocket Thrust Coefficient Tables (Gamma = 1.4)

e	Expansion area ratio
Me:	Mach number at exit plane
pe/pc:	Ratio of pressure at exit plane to chamber pressure
Cf-opt:	Thrust coefficient assuming optimal expansion
Cfv:	Vacuum thrust coefficient

epsilon M_e p_e/p_c C_f-opt C_fv

1.0 1.000 0.5281116 0.73976 1.26788

2.0 2.197 0.0939326 1.26973 1.45760

3.0 2.637 0.0472987 1.38183 1.52373

4.0 2.940 0.0297870 1.44199 1.56114

5.0 3.175 0.0209927 1.48113 1.58609

6.0 3.368 0.0158407 1.50926 1.60431

7.0 3.533 0.0125155 1.53077 1.61837

8.0 3.677 0.0102208 1.54791 1.62968

9.0 3.806 0.0085578 1.56200 1.63902

10.0 3.923 0.0073064 1.57387 1.64693

11.0 4.029 0.0063363 1.58403 1.65373

12.0 4.127 0.0055661 1.59288 1.65967

13.0 4.218 0.0049421 1.60066 1.66491

14.0 4.304 0.0044282 1.60759 1.66959

15.0 4.384 0.0039988 1.61381 1.67380

16.0 4.459 0.0036356 1.61944 1.67761

17.0 4.531 0.0033251 1.62456 1.68108

18.0 4.599 0.0030570 1.62925 1.68427

19.0 4.664 0.0028237 1.63356 1.68721

20.0 4.725 0.0026190 1.63755 1.68993

epsilon M_e p_e/p_c C_f-opt C_fv

21.0 4.785 0.0024384 1.64125 1.69246

22.0 4.842 0.0022780 1.64470 1.69481

23.0 4.896 0.0021347 1.64792 1.69702

24.0 4.949 0.0020060 1.65094 1.69909

25.0 5.000 0.0018900 1.65378 1.70103

26.0 5.049 0.0017850 1.65646 1.70287

27.0 5.097 0.0016895 1.65899 1.70461

28.0 5.143 0.0016024 1.66138 1.70625

29.0 5.188 0.0015227 1.66366 1.70781

30.0 5.231 0.0014495 1.66582 1.70930

31.0 5.273 0.0013820 1.66787 1.71072

32.0 5.314 0.0013198 1.66983 1.71207

33.0 5.354 0.0012622 1.67171 1.71336

34.0 5.393 0.0012087 1.67350 1.71459

35.0 5.431 0.0011589 1.67521 1.71578

36.0 5.468 0.0011126 1.67686 1.71691

37.0 5.505 0.0010693 1.67844 1.71800

38.0 5.540 0.0010288 1.67996 1.71905

39.0 5.575 0.0009909 1.68142 1.72006

40.0 5.609 0.0009553 1.68282 1.72103

epsilon M_e p_e/p_c C_f-opt C_fv

41.0 5.642 0.0009218 1.68418 1.72197

42.0 5.675 0.0008902 1.68549 1.72288

43.0 5.706 0.0008605 1.68675 1.72375

44.0 5.738 0.0008324 1.68797 1.72460

45.0 5.768 0.0008058 1.68916 1.72542

46.0 5.799 0.0007806 1.69030 1.72621

47.0 5.828 0.0007568 1.69141 1.72698

48.0 5.857 0.0007341 1.69249 1.72772

49.0 5.886 0.0007126 1.69353 1.72845

50.0 5.914 0.0006922 1.69454 1.72915

52.0 5.969 0.0006542 1.69648 1.73050

54.0 6.022 0.0006196 1.69831 1.73177

56.0 6.073 0.0005880 1.70005 1.73298

58.0 6.123 0.0005590 1.70170 1.73412

60.0 6.171 0.0005324 1.70327 1.73521

62.0 6.218 0.0005079 1.70476 1.73625

64.0 6.264 0.0004853 1.70619 1.73725

66.0 6.309 0.0004643 1.70755 1.73820

68.0 6.353 0.0004448 1.70886 1.73910

70.0 6.395 0.0004267 1.71011 1.73998

epsilon M_e p_e/p_c C_f-opt C_fv

72.0 6.437 0.0004098 1.71131 1.74081

74.0 6.477 0.0003940 1.71246 1.74162

76.0 6.517 0.0003792 1.71357 1.74239

78.0 6.556 0.0003653 1.71464 1.74313

80.0 6.594 0.0003523 1.71567 1.74385

82.0 6.631 0.0003401 1.71666 1.74454

84.0 6.668 0.0003285 1.71762 1.74521

86.0 6.703 0.0003176 1.71854 1.74586

88.0 6.739 0.0003074 1.71944 1.74648

90.0 6.773 0.0002976 1.72030 1.74709

95.0 6.856 0.0002755 1.72235 1.74852

100.0 6.936 0.0002560 1.72425 1.74985

105.0 7.013 0.0002387 1.72601 1.75108

110.0 7.087 0.0002234 1.72766 1.75224

115.0 7.158 0.0002096 1.72921 1.75332

120.0 7.226 0.0001973 1.73066 1.75434

125.0 7.292 0.0001861 1.73203 1.75529

130.0 7.356 0.0001760 1.73332 1.75620

135.0 7.418 0.0001668 1.73454 1.75706

140.0 7.478 0.0001583 1.73570 1.75787

epsilon M_e p_e/p_c C_f-opt C_fv

145.0 7.537 0.0001506 1.73680 1.75864

150.0 7.593 0.0001435 1.73785 1.75938

155.0 7.649 0.0001370 1.73885 1.76008

160.0 7.702 0.0001309 1.73980 1.76075

165.0 7.755 0.0001253 1.74071 1.76139

170.0 7.806 0.0001201 1.74158 1.76200

175.0 7.856 0.0001152 1.74242 1.76259

180.0 7.905 0.0001107 1.74322 1.76315

185.0 7.952 0.0001065 1.74400 1.76370

190.0 7.999 0.0001025 1.74474 1.76422

200.0 8.089 0.0000953 1.74615 1.76521

210.0 8.176 0.0000889 1.74745 1.76613

220.0 8.259 0.0000832 1.74868 1.76699

230.0 8.340 0.0000781 1.74982 1.76779

240.0 8.417 0.0000736 1.75090 1.76855

250.0 8.492 0.0000694 1.75191 1.76927

260.0 8.565 0.0000657 1.75287 1.76994

270.0 8.635 0.0000622 1.75378 1.77058

280.0 8.703 0.0000591 1.75464 1.77119

290.0 8.769 0.0000562 1.75546 1.77176

epsilon M_e p_e/p_c C_f-opt C_fv

Rayleigh Flow : Thrust Coefficient (gamma = 1.3)