NACA 16-018 (naca16018-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16-018 (naca16018-il) Reynolds number: 100,000 Max Cl/Cd: 24.43 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16018-il-100000-n5.txt Download as CSV file: xf-naca16018-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-018
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7089 0.12474 0.11921 -0.0598 1.0000 0.0380
-16.250 -0.7569 0.11154 0.10589 -0.0662 1.0000 0.0375
-16.000 -0.7983 0.10175 0.09595 -0.0699 1.0000 0.0372
-15.750 -0.8356 0.09405 0.08806 -0.0717 1.0000 0.0370
-15.500 -0.8698 0.08774 0.08155 -0.0718 1.0000 0.0369
-15.250 -0.9013 0.08242 0.07601 -0.0707 1.0000 0.0369
-15.000 -0.9310 0.07780 0.07115 -0.0686 1.0000 0.0371
-14.750 -0.9584 0.07379 0.06688 -0.0658 1.0000 0.0373
-14.500 -0.9844 0.07017 0.06299 -0.0622 1.0000 0.0376
-14.250 -1.0087 0.06695 0.05947 -0.0581 1.0000 0.0379
-14.000 -1.0283 0.06419 0.05645 -0.0538 1.0000 0.0383
-13.750 -1.0328 0.06233 0.05455 -0.0508 1.0000 0.0389
-13.500 -1.0393 0.06062 0.05275 -0.0474 1.0000 0.0395
-13.250 -1.0461 0.05893 0.05093 -0.0437 1.0000 0.0402
-13.000 -1.0528 0.05722 0.04907 -0.0399 1.0000 0.0409
-12.750 -1.0586 0.05549 0.04716 -0.0359 1.0000 0.0416
-12.500 -1.0632 0.05383 0.04528 -0.0319 1.0000 0.0425
-12.250 -1.0664 0.05223 0.04345 -0.0279 1.0000 0.0436
-12.000 -1.0687 0.05066 0.04159 -0.0239 1.0000 0.0448
-11.750 -1.0696 0.04917 0.03977 -0.0199 1.0000 0.0458
-11.500 -1.0512 0.04761 0.03820 -0.0196 0.9990 0.0472
-11.250 -1.0342 0.04635 0.03686 -0.0190 0.9975 0.0487
-11.000 -1.0169 0.04517 0.03553 -0.0184 0.9959 0.0505
-10.750 -0.9964 0.04398 0.03411 -0.0181 0.9944 0.0527
-10.500 -0.9737 0.04282 0.03267 -0.0180 0.9929 0.0547
-10.250 -0.9497 0.04161 0.03148 -0.0183 0.9915 0.0566
-10.000 -0.9309 0.04071 0.03055 -0.0177 0.9898 0.0588
-9.750 -0.9102 0.03986 0.02959 -0.0173 0.9882 0.0614
-9.500 -0.8867 0.03902 0.02860 -0.0173 0.9866 0.0640
-9.250 -0.8633 0.03813 0.02765 -0.0173 0.9852 0.0663
-9.000 -0.8434 0.03733 0.02685 -0.0170 0.9836 0.0694
-8.750 -0.8278 0.03658 0.02603 -0.0155 0.9811 0.0729
-8.500 -0.8109 0.03590 0.02523 -0.0142 0.9790 0.0766
-8.250 -0.7963 0.03506 0.02443 -0.0127 0.9768 0.0804
-8.000 -0.7787 0.03437 0.02369 -0.0117 0.9748 0.0855
-7.750 -0.7598 0.03370 0.02299 -0.0109 0.9730 0.0924
-7.500 -0.7491 0.03303 0.02231 -0.0084 0.9698 0.1005
-7.250 -0.7372 0.03237 0.02169 -0.0061 0.9671 0.1107
-7.000 -0.7221 0.03174 0.02111 -0.0044 0.9645 0.1252
-6.750 -0.7042 0.03113 0.02057 -0.0034 0.9623 0.1465
-6.500 -0.6856 0.03047 0.02008 -0.0025 0.9606 0.1793
-6.250 -0.6808 0.02977 0.01959 0.0013 0.9568 0.2157
-6.000 -0.6733 0.02894 0.01911 0.0045 0.9535 0.2756
-5.750 -0.6675 0.02789 0.01862 0.0080 0.9505 0.3674
-5.500 -0.6559 0.02688 0.01855 0.0108 0.9486 0.5204
-5.250 -0.5577 0.03023 0.02272 0.0006 0.9514 0.6988
-5.000 -0.5315 0.03087 0.02326 0.0012 0.9493 0.7284
-4.750 -0.5116 0.03117 0.02343 0.0028 0.9473 0.7511
-4.500 -0.4991 0.03162 0.02380 0.0061 0.9430 0.7672
-4.250 -0.4790 0.03222 0.02429 0.0080 0.9395 0.7824
-4.000 -0.4507 0.03315 0.02511 0.0084 0.9373 0.7975
-3.750 -0.4121 0.03455 0.02641 0.0072 0.9359 0.8130
-3.500 -0.3579 0.03601 0.02774 0.0027 0.9353 0.8215
-3.250 -0.3279 0.03630 0.02792 0.0019 0.9336 0.8304
-3.000 -0.2935 0.03664 0.02816 0.0002 0.9315 0.8351
-2.750 -0.2886 0.03660 0.02807 0.0042 0.9263 0.8444
-2.500 -0.2532 0.03683 0.02822 0.0022 0.9240 0.8476
-2.250 -0.2238 0.03690 0.02821 0.0012 0.9215 0.8528
-2.000 -0.2009 0.03682 0.02806 0.0014 0.9193 0.8595
-1.750 -0.1622 0.03695 0.02813 -0.0015 0.9180 0.8621
-1.500 -0.1487 0.03707 0.02823 0.0008 0.9124 0.8673
-1.250 -0.1348 0.03698 0.02809 0.0029 0.9083 0.8742
-1.000 -0.0990 0.03705 0.02813 0.0005 0.9062 0.8765
-0.750 -0.0638 0.03707 0.02812 -0.0017 0.9043 0.8794
-0.250 -0.0337 0.03707 0.02810 0.0020 0.8948 0.8898
0.000 0.0000 0.03709 0.02812 0.0000 0.8920 0.8920
0.250 0.0337 0.03707 0.02810 -0.0020 0.8898 0.8948
0.750 0.0638 0.03707 0.02812 0.0017 0.8794 0.9044
1.000 0.0990 0.03705 0.02813 -0.0005 0.8765 0.9062
1.250 0.1348 0.03697 0.02809 -0.0029 0.8742 0.9084
1.500 0.1487 0.03707 0.02822 -0.0008 0.8674 0.9124
1.750 0.1622 0.03694 0.02813 0.0015 0.8621 0.9180
2.000 0.2009 0.03681 0.02805 -0.0014 0.8595 0.9193
2.250 0.2240 0.03689 0.02820 -0.0012 0.8529 0.9215
2.500 0.2532 0.03682 0.02821 -0.0022 0.8476 0.9240
2.750 0.2885 0.03659 0.02806 -0.0042 0.8444 0.9264
3.000 0.2931 0.03662 0.02814 -0.0001 0.8351 0.9316
3.250 0.3280 0.03628 0.02791 -0.0019 0.8305 0.9336
3.500 0.3582 0.03599 0.02772 -0.0027 0.8216 0.9354
3.750 0.4122 0.03454 0.02639 -0.0072 0.8130 0.9359
4.000 0.4508 0.03313 0.02509 -0.0084 0.7976 0.9373
4.500 0.4990 0.03161 0.02379 -0.0061 0.7672 0.9431
4.750 0.5118 0.03115 0.02341 -0.0028 0.7512 0.9473
5.000 0.5319 0.03085 0.02324 -0.0013 0.7285 0.9493
5.250 0.5580 0.03020 0.02269 -0.0006 0.6988 0.9514
5.500 0.6563 0.02686 0.01853 -0.0109 0.5191 0.9486
5.750 0.6677 0.02788 0.01860 -0.0080 0.3668 0.9505
6.000 0.6736 0.02892 0.01910 -0.0045 0.2756 0.9536
6.250 0.6809 0.02975 0.01957 -0.0013 0.2156 0.9568
6.500 0.6860 0.03045 0.02006 0.0024 0.1791 0.9606
6.750 0.7046 0.03111 0.02055 0.0033 0.1463 0.9624
7.000 0.7225 0.03172 0.02109 0.0043 0.1251 0.9646
7.250 0.7376 0.03235 0.02167 0.0060 0.1106 0.9671
7.500 0.7493 0.03301 0.02229 0.0083 0.1005 0.9699
7.750 0.7604 0.03368 0.02297 0.0108 0.0924 0.9730
8.000 0.7792 0.03435 0.02367 0.0115 0.0855 0.9748
8.250 0.7968 0.03504 0.02440 0.0126 0.0804 0.9769
8.500 0.8114 0.03588 0.02521 0.0141 0.0766 0.9791
8.750 0.8283 0.03656 0.02601 0.0154 0.0729 0.9812
9.000 0.8438 0.03731 0.02682 0.0169 0.0694 0.9838
9.250 0.8641 0.03811 0.02762 0.0172 0.0663 0.9853
9.500 0.8876 0.03900 0.02858 0.0171 0.0639 0.9867
9.750 0.9110 0.03983 0.02957 0.0171 0.0613 0.9883
10.000 0.9317 0.04069 0.03053 0.0176 0.0588 0.9899
10.250 0.9504 0.04159 0.03145 0.0182 0.0565 0.9916
10.500 0.9746 0.04279 0.03265 0.0179 0.0547 0.9930
10.750 0.9974 0.04396 0.03409 0.0179 0.0527 0.9945
11.000 1.0178 0.04515 0.03550 0.0182 0.0505 0.9960
11.250 1.0352 0.04632 0.03684 0.0188 0.0486 0.9976
11.500 1.0522 0.04758 0.03818 0.0194 0.0472 0.9991
11.750 1.0701 0.04914 0.03974 0.0198 0.0458 1.0000
12.000 1.0692 0.05063 0.04156 0.0239 0.0448 1.0000
12.250 1.0668 0.05220 0.04341 0.0279 0.0436 1.0000
12.500 1.0636 0.05379 0.04523 0.0319 0.0425 1.0000
12.750 1.0591 0.05545 0.04711 0.0358 0.0416 1.0000
13.000 1.0533 0.05717 0.04901 0.0398 0.0408 1.0000
13.250 1.0467 0.05886 0.05086 0.0437 0.0401 1.0000
13.500 1.0399 0.06055 0.05268 0.0474 0.0395 1.0000
13.750 1.0336 0.06226 0.05447 0.0508 0.0389 1.0000
14.000 1.0294 0.06411 0.05637 0.0537 0.0383 1.0000
14.250 1.0089 0.06691 0.05943 0.0581 0.0379 1.0000
14.500 0.9847 0.07012 0.06294 0.0622 0.0375 1.0000
14.750 0.9586 0.07373 0.06683 0.0658 0.0372 1.0000
15.000 0.9314 0.07775 0.07110 0.0686 0.0370 1.0000
15.250 0.9020 0.08233 0.07591 0.0707 0.0369 1.0000
15.500 0.8703 0.08767 0.08148 0.0718 0.0369 1.0000
15.750 0.8360 0.09399 0.08800 0.0717 0.0369 1.0000
16.000 0.7986 0.10173 0.09593 0.0699 0.0372 1.0000
16.250 0.7567 0.11162 0.10597 0.0661 0.0375 1.0000
16.500 0.7084 0.12499 0.11945 0.0597 0.0380 1.0000
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Polar data table (+)
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