FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: FX 38-153 AIRFOIL (fx38153-il) Reynolds number: 500,000 Max Cl/Cd: 63.29 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx38153-il-500000.txt Download as CSV file: xf-fx38153-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 38-153 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3855 0.08931 0.08694 -0.0928 0.9788 0.0189
-11.250 -0.4188 0.07663 0.07416 -0.1021 0.9755 0.0188
-11.000 -0.4410 0.06977 0.06716 -0.1065 0.9732 0.0188
-10.750 -0.4561 0.06472 0.06197 -0.1092 0.9714 0.0188
-10.500 -0.4674 0.06059 0.05771 -0.1107 0.9700 0.0189
-10.250 -0.4953 0.05894 0.05598 -0.1051 0.9641 0.0189
-10.000 -0.5110 0.05645 0.05337 -0.1026 0.9597 0.0190
-9.750 -0.5208 0.05389 0.05067 -0.1008 0.9569 0.0192
-9.500 -0.5189 0.05077 0.04738 -0.1009 0.9550 0.0194
-7.750 -0.5295 0.03016 0.02456 -0.0741 0.9272 0.0151
-7.500 -0.5035 0.02687 0.02095 -0.0736 0.9267 0.0127
-7.250 -0.4754 0.02454 0.01823 -0.0733 0.9263 0.0120
-7.000 -0.4457 0.02344 0.01703 -0.0739 0.9258 0.0121
-6.750 -0.4153 0.02252 0.01603 -0.0747 0.9253 0.0123
-6.500 -0.4288 0.02238 0.01585 -0.0668 0.9167 0.0123
-6.250 -0.4031 0.02160 0.01503 -0.0667 0.9149 0.0125
-6.000 -0.3746 0.02091 0.01430 -0.0673 0.9135 0.0128
-5.750 -0.3444 0.02036 0.01371 -0.0682 0.9124 0.0135
-5.500 -0.3139 0.01976 0.01307 -0.0691 0.9116 0.0139
-5.250 -0.2829 0.01909 0.01237 -0.0703 0.9108 0.0141
-5.000 -0.2829 0.01895 0.01221 -0.0652 0.9041 0.0142
-4.750 -0.2599 0.01847 0.01170 -0.0648 0.9010 0.0144
-4.500 -0.2297 0.01780 0.01102 -0.0658 0.8992 0.0148
-4.250 -0.1967 0.01725 0.01045 -0.0673 0.8980 0.0157
-4.000 -0.1624 0.01681 0.00998 -0.0690 0.8971 0.0173
-3.750 -0.1276 0.01633 0.00945 -0.0708 0.8964 0.0216
-3.500 -0.0921 0.01592 0.00912 -0.0728 0.8957 0.0404
-3.250 -0.0810 0.01580 0.00910 -0.0700 0.8890 0.0646
-3.000 -0.0496 0.01536 0.00878 -0.0713 0.8861 0.1068
-2.750 -0.0093 0.01421 0.00826 -0.0752 0.8850 0.2653
-2.500 0.0573 0.01201 0.00762 -0.0863 0.8866 0.6427
-2.250 0.0911 0.01189 0.00770 -0.0873 0.8849 0.7051
-2.000 0.1257 0.01189 0.00773 -0.0884 0.8836 0.7346
-1.750 0.1604 0.01189 0.00771 -0.0895 0.8826 0.7488
-1.500 0.1929 0.01200 0.00783 -0.0899 0.8817 0.7603
-1.250 0.2299 0.01195 0.00775 -0.0917 0.8810 0.7673
-1.000 0.2643 0.01189 0.00768 -0.0926 0.8802 0.7724
-0.750 0.2713 0.01215 0.00797 -0.0879 0.8714 0.7763
-0.500 0.3115 0.01186 0.00766 -0.0899 0.8694 0.7833
-0.250 0.3454 0.01169 0.00750 -0.0901 0.8673 0.7879
0.000 0.3792 0.01160 0.00742 -0.0904 0.8654 0.7910
0.250 0.3904 0.01173 0.00757 -0.0866 0.8570 0.7953
0.500 0.4266 0.01153 0.00734 -0.0882 0.8534 0.8016
0.750 0.4588 0.01144 0.00726 -0.0883 0.8504 0.8036
1.000 0.4670 0.01144 0.00729 -0.0838 0.8400 0.8058
1.250 0.4932 0.01121 0.00705 -0.0833 0.8313 0.8076
1.500 0.5239 0.01095 0.00676 -0.0839 0.8210 0.8093
1.750 0.5460 0.01077 0.00657 -0.0829 0.8076 0.8119
2.000 0.5786 0.01058 0.00635 -0.0844 0.7939 0.8149
2.250 0.6114 0.01044 0.00615 -0.0857 0.7787 0.8169
2.500 0.6384 0.01038 0.00604 -0.0855 0.7603 0.8179
2.750 0.6607 0.01044 0.00597 -0.0843 0.7287 0.8192
3.000 0.6741 0.01068 0.00601 -0.0811 0.6819 0.8209
3.250 0.6828 0.01106 0.00615 -0.0772 0.6321 0.8231
3.500 0.6948 0.01146 0.00632 -0.0743 0.5886 0.8252
3.750 0.7110 0.01188 0.00653 -0.0726 0.5444 0.8273
4.000 0.7299 0.01234 0.00679 -0.0716 0.4989 0.8295
4.250 0.7520 0.01287 0.00707 -0.0714 0.4525 0.8319
4.750 0.7846 0.01371 0.00760 -0.0678 0.3791 0.8343
5.000 0.8026 0.01416 0.00789 -0.0664 0.3449 0.8354
5.250 0.8224 0.01455 0.00817 -0.0654 0.3159 0.8365
5.500 0.8413 0.01500 0.00849 -0.0642 0.2857 0.8378
5.750 0.8611 0.01544 0.00882 -0.0632 0.2561 0.8394
6.000 0.8805 0.01598 0.00918 -0.0623 0.2238 0.8409
6.500 0.9250 0.01688 0.00987 -0.0617 0.1770 0.8438
6.750 0.9489 0.01730 0.01023 -0.0617 0.1608 0.8455
7.250 0.9938 0.01825 0.01102 -0.0613 0.1262 0.8479
7.500 1.0148 0.01857 0.01135 -0.0606 0.1167 0.8488
7.750 1.0342 0.01903 0.01177 -0.0597 0.1021 0.8497
8.000 1.0533 0.01951 0.01222 -0.0587 0.0916 0.8507
8.250 1.0722 0.01999 0.01270 -0.0576 0.0844 0.8519
8.500 1.0924 0.02042 0.01316 -0.0569 0.0746 0.8532
8.750 1.1089 0.02114 0.01379 -0.0556 0.0593 0.8544
9.000 1.1271 0.02177 0.01442 -0.0547 0.0514 0.8555
9.250 1.1464 0.02235 0.01502 -0.0540 0.0411 0.8567
9.500 1.1615 0.02324 0.01583 -0.0527 0.0324 0.8579
9.750 1.1791 0.02399 0.01661 -0.0518 0.0291 0.8590
10.000 1.1954 0.02485 0.01751 -0.0508 0.0263 0.8602
10.250 1.2144 0.02551 0.01825 -0.0502 0.0250 0.8612
10.500 1.2329 0.02624 0.01905 -0.0496 0.0238 0.8622
10.750 1.2487 0.02697 0.01985 -0.0484 0.0225 0.8632
11.000 1.2624 0.02779 0.02072 -0.0470 0.0213 0.8643
11.250 1.2758 0.02865 0.02164 -0.0455 0.0203 0.8654
11.500 1.2904 0.02944 0.02252 -0.0443 0.0195 0.8665
11.750 1.3046 0.03032 0.02345 -0.0432 0.0187 0.8675
12.000 1.3182 0.03126 0.02445 -0.0420 0.0181 0.8685
12.250 1.3305 0.03230 0.02557 -0.0408 0.0175 0.8696
12.500 1.3417 0.03347 0.02680 -0.0395 0.0169 0.8708
12.750 1.3508 0.03483 0.02824 -0.0381 0.0164 0.8719
13.000 1.3615 0.03611 0.02961 -0.0370 0.0161 0.8730
13.250 1.3714 0.03749 0.03109 -0.0359 0.0158 0.8741
13.500 1.3804 0.03898 0.03267 -0.0348 0.0154 0.8752
13.750 1.3887 0.04059 0.03438 -0.0338 0.0151 0.8762
14.000 1.3957 0.04238 0.03626 -0.0329 0.0146 0.8773
14.250 1.3995 0.04434 0.03830 -0.0317 0.0141 0.8784
14.500 1.4000 0.04666 0.04072 -0.0304 0.0136 0.8795
14.750 1.3985 0.04930 0.04348 -0.0292 0.0132 0.8805
15.000 1.3991 0.05187 0.04618 -0.0284 0.0129 0.8815
15.250 1.4026 0.05422 0.04867 -0.0279 0.0126 0.8825
15.500 1.4042 0.05689 0.05148 -0.0275 0.0123 0.8836
15.750 1.4041 0.05985 0.05456 -0.0274 0.0119 0.8846
16.000 1.4018 0.06320 0.05805 -0.0274 0.0115 0.8857
16.250 1.3969 0.06700 0.06198 -0.0278 0.0111 0.8867
16.500 1.3883 0.07146 0.06657 -0.0285 0.0107 0.8877
16.750 1.3755 0.07663 0.07186 -0.0295 0.0104 0.8888
17.000 1.3622 0.08204 0.07740 -0.0309 0.0102 0.8898
17.250 1.3512 0.08732 0.08283 -0.0325 0.0100 0.8907
17.500 1.3511 0.09125 0.08692 -0.0341 0.0096 0.8917
17.750 1.3464 0.09587 0.09170 -0.0360 0.0093 0.8925
18.000 1.3383 0.10096 0.09695 -0.0380 0.0089 0.8933
18.250 1.3287 0.10635 0.10248 -0.0403 0.0085 0.8941
18.500 1.3173 0.11216 0.10843 -0.0429 0.0082 0.8949
18.750 1.3055 0.11813 0.11452 -0.0457 0.0081 0.8957
19.000 1.2931 0.12432 0.12084 -0.0488 0.0079 0.8965
19.250 1.2804 0.13064 0.12728 -0.0521 0.0077 0.8973
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