NACA 0018 (naca0018-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0018 (naca0018-il) Reynolds number: 100,000 Max Cl/Cd: 38.08 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0018-il-100000-n5.txt Download as CSV file: xf-naca0018-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0018
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
------ -------- --------- --------- -------- -------- --------
-18.500 -0.7056 0.18357 0.17707 0.0125 1.0000 0.0618
-18.250 -0.7312 0.17080 0.16428 0.0055 1.0000 0.0645
-18.000 -0.9311 0.11971 0.11273 -0.0226 1.0000 0.0715
-17.750 -0.8775 0.12672 0.11994 -0.0180 1.0000 0.0724
-17.500 -0.9340 0.11189 0.10487 -0.0263 1.0000 0.0739
-17.250 -0.9703 0.10170 0.09444 -0.0319 1.0000 0.0750
-17.000 -0.9964 0.09376 0.08627 -0.0360 1.0000 0.0762
-16.750 -1.0179 0.08687 0.07915 -0.0393 1.0000 0.0774
-16.500 -1.0368 0.08065 0.07266 -0.0420 1.0000 0.0787
-16.250 -1.0350 0.07781 0.06981 -0.0428 1.0000 0.0800
-16.000 -1.0347 0.07477 0.06674 -0.0436 1.0000 0.0814
-15.750 -1.0376 0.07129 0.06317 -0.0447 1.0000 0.0829
-15.500 -1.0423 0.06764 0.05938 -0.0457 1.0000 0.0847
-15.250 -1.0483 0.06390 0.05543 -0.0467 1.0000 0.0866
-15.000 -1.0476 0.06116 0.05264 -0.0471 1.0000 0.0883
-14.750 -1.0458 0.05865 0.05012 -0.0474 1.0000 0.0902
-14.500 -1.0455 0.05600 0.04739 -0.0476 1.0000 0.0924
-14.250 -1.0455 0.05332 0.04456 -0.0478 1.0000 0.0949
-14.000 -1.0432 0.05097 0.04213 -0.0477 1.0000 0.0972
-13.750 -1.0400 0.04886 0.04001 -0.0474 1.0000 0.0995
-13.500 -1.0370 0.04675 0.03783 -0.0471 1.0000 0.1023
-13.250 -1.0334 0.04471 0.03564 -0.0466 1.0000 0.1055
-13.000 -1.0290 0.04288 0.03381 -0.0459 1.0000 0.1083
-12.750 -1.0244 0.04115 0.03206 -0.0451 1.0000 0.1114
-12.500 -1.0188 0.03952 0.03032 -0.0442 1.0000 0.1152
-12.250 -1.0130 0.03798 0.02875 -0.0431 1.0000 0.1188
-12.000 -1.0075 0.03656 0.02732 -0.0418 1.0000 0.1225
-11.750 -1.0004 0.03526 0.02592 -0.0404 1.0000 0.1270
-11.500 -0.9938 0.03402 0.02469 -0.0387 1.0000 0.1311
-11.250 -0.9874 0.03289 0.02354 -0.0369 1.0000 0.1357
-10.750 -0.9734 0.03089 0.02149 -0.0327 1.0000 0.1457
-10.500 -0.9663 0.03003 0.02059 -0.0303 1.0000 0.1513
-10.250 -0.9601 0.02923 0.01978 -0.0275 1.0000 0.1567
-10.000 -0.9563 0.02851 0.01908 -0.0242 1.0000 0.1622
-9.500 -0.9495 0.02730 0.01788 -0.0168 1.0000 0.1737
-9.250 -0.9431 0.02674 0.01730 -0.0135 1.0000 0.1807
-9.000 -0.9370 0.02618 0.01677 -0.0101 1.0000 0.1871
-8.750 -0.9302 0.02567 0.01626 -0.0068 1.0000 0.1945
-8.500 -0.9225 0.02517 0.01578 -0.0036 1.0000 0.2020
-8.250 -0.9148 0.02471 0.01533 -0.0004 1.0000 0.2100
-8.000 -0.9059 0.02426 0.01490 0.0027 1.0000 0.2182
-7.750 -0.8967 0.02384 0.01450 0.0057 1.0000 0.2271
-7.500 -0.8867 0.02344 0.01412 0.0085 1.0000 0.2360
-7.250 -0.8758 0.02308 0.01376 0.0112 1.0000 0.2460
-7.000 -0.8647 0.02271 0.01345 0.0138 1.0000 0.2554
-6.750 -0.8322 0.02229 0.01303 0.0123 0.9948 0.2695
-6.500 -0.7975 0.02189 0.01264 0.0104 0.9886 0.2846
-6.250 -0.7628 0.02150 0.01230 0.0085 0.9820 0.2997
-6.000 -0.7292 0.02113 0.01198 0.0069 0.9750 0.3149
-5.750 -0.6943 0.02078 0.01168 0.0052 0.9681 0.3307
-5.500 -0.6612 0.02045 0.01139 0.0038 0.9604 0.3466
-5.250 -0.6261 0.02013 0.01111 0.0021 0.9531 0.3631
-5.000 -0.5924 0.01983 0.01083 0.0008 0.9453 0.3797
-4.750 -0.5579 0.01953 0.01057 -0.0007 0.9374 0.3969
-4.500 -0.5239 0.01923 0.01033 -0.0019 0.9297 0.4135
-4.250 -0.4925 0.01894 0.01011 -0.0026 0.9201 0.4294
-4.000 -0.4597 0.01866 0.00989 -0.0035 0.9116 0.4456
-3.750 -0.4292 0.01840 0.00967 -0.0038 0.9013 0.4616
-3.500 -0.3983 0.01815 0.00945 -0.0042 0.8913 0.4779
-3.000 -0.3390 0.01768 0.00907 -0.0044 0.8692 0.5102
-2.750 -0.3069 0.01743 0.00887 -0.0049 0.8592 0.5264
-2.500 -0.2803 0.01725 0.00874 -0.0043 0.8457 0.5421
-2.250 -0.2501 0.01704 0.00855 -0.0044 0.8343 0.5585
-2.000 -0.2221 0.01686 0.00839 -0.0040 0.8210 0.5752
-1.750 -0.1947 0.01672 0.00830 -0.0035 0.8069 0.5908
-1.500 -0.1654 0.01656 0.00818 -0.0033 0.7939 0.6068
-1.250 -0.1373 0.01643 0.00807 -0.0028 0.7796 0.6228
-1.000 -0.1106 0.01634 0.00800 -0.0022 0.7641 0.6391
-0.750 -0.0833 0.01626 0.00791 -0.0016 0.7492 0.6558
-0.500 -0.0545 0.01619 0.00786 -0.0012 0.7347 0.6714
-0.250 -0.0269 0.01616 0.00785 -0.0006 0.7189 0.6869
0.000 0.0000 0.01616 0.00786 0.0000 0.7027 0.7027
0.250 0.0269 0.01616 0.00785 0.0006 0.6869 0.7189
0.500 0.0545 0.01619 0.00786 0.0012 0.6714 0.7347
0.750 0.0833 0.01626 0.00791 0.0016 0.6558 0.7492
1.000 0.1106 0.01634 0.00800 0.0022 0.6391 0.7641
1.250 0.1373 0.01643 0.00807 0.0028 0.6228 0.7796
1.500 0.1654 0.01656 0.00818 0.0033 0.6068 0.7939
1.750 0.1947 0.01672 0.00830 0.0035 0.5908 0.8069
2.000 0.2221 0.01686 0.00839 0.0040 0.5752 0.8210
2.250 0.2501 0.01704 0.00855 0.0044 0.5585 0.8343
2.500 0.2803 0.01725 0.00874 0.0043 0.5421 0.8457
2.750 0.3069 0.01743 0.00887 0.0049 0.5264 0.8592
3.000 0.3390 0.01768 0.00907 0.0044 0.5102 0.8692
3.500 0.3983 0.01815 0.00945 0.0043 0.4779 0.8914
3.750 0.4291 0.01840 0.00966 0.0038 0.4616 0.9013
4.000 0.4596 0.01866 0.00988 0.0035 0.4456 0.9116
4.250 0.4925 0.01894 0.01011 0.0026 0.4294 0.9201
4.500 0.5238 0.01923 0.01033 0.0019 0.4135 0.9297
4.750 0.5579 0.01953 0.01056 0.0007 0.3969 0.9374
5.000 0.5924 0.01982 0.01083 -0.0008 0.3797 0.9454
5.250 0.6261 0.02012 0.01110 -0.0021 0.3631 0.9532
5.500 0.6612 0.02044 0.01138 -0.0038 0.3466 0.9605
5.750 0.6944 0.02077 0.01168 -0.0052 0.3307 0.9681
6.000 0.7293 0.02113 0.01198 -0.0070 0.3149 0.9751
6.250 0.7630 0.02150 0.01230 -0.0086 0.2997 0.9821
6.500 0.7976 0.02189 0.01264 -0.0104 0.2845 0.9887
6.750 0.8324 0.02228 0.01303 -0.0123 0.2694 0.9949
7.000 0.8645 0.02270 0.01344 -0.0138 0.2555 1.0000
7.250 0.8756 0.02307 0.01375 -0.0112 0.2460 1.0000
7.500 0.8865 0.02343 0.01411 -0.0085 0.2360 1.0000
7.750 0.8966 0.02384 0.01449 -0.0056 0.2271 1.0000
8.000 0.9058 0.02425 0.01489 -0.0026 0.2182 1.0000
8.250 0.9147 0.02470 0.01532 0.0004 0.2100 1.0000
8.500 0.9225 0.02517 0.01577 0.0036 0.2020 1.0000
8.750 0.9302 0.02566 0.01625 0.0068 0.1945 1.0000
9.000 0.9371 0.02617 0.01676 0.0101 0.1871 1.0000
9.250 0.9432 0.02673 0.01729 0.0135 0.1807 1.0000
9.500 0.9497 0.02729 0.01787 0.0168 0.1737 1.0000
10.000 0.9566 0.02851 0.01908 0.0241 0.1622 1.0000
10.250 0.9605 0.02922 0.01977 0.0274 0.1567 1.0000
10.500 0.9668 0.03002 0.02058 0.0302 0.1512 1.0000
10.750 0.9739 0.03088 0.02148 0.0326 0.1456 1.0000
11.000 0.9794 0.03188 0.02241 0.0349 0.1411 1.0000
11.250 0.9881 0.03288 0.02353 0.0368 0.1356 1.0000
11.500 0.9946 0.03402 0.02467 0.0386 0.1311 1.0000
11.750 1.0013 0.03525 0.02591 0.0402 0.1269 1.0000
12.000 1.0085 0.03655 0.02730 0.0416 0.1224 1.0000
12.250 1.0140 0.03797 0.02873 0.0429 0.1187 1.0000
12.500 1.0199 0.03950 0.03030 0.0440 0.1151 1.0000
12.750 1.0256 0.04113 0.03203 0.0450 0.1113 1.0000
13.000 1.0302 0.04286 0.03379 0.0457 0.1082 1.0000
13.250 1.0348 0.04469 0.03562 0.0464 0.1054 1.0000
13.500 1.0385 0.04672 0.03780 0.0469 0.1022 1.0000
13.750 1.0416 0.04883 0.03998 0.0472 0.0994 1.0000
14.000 1.0450 0.05093 0.04208 0.0474 0.0971 1.0000
14.250 1.0471 0.05330 0.04454 0.0475 0.0948 1.0000
14.500 1.0473 0.05597 0.04735 0.0474 0.0923 1.0000
14.750 1.0478 0.05860 0.05007 0.0471 0.0901 1.0000
15.000 1.0497 0.06109 0.05257 0.0469 0.0883 1.0000
15.250 1.0501 0.06388 0.05543 0.0464 0.0865 1.0000
15.500 1.0444 0.06760 0.05934 0.0455 0.0846 1.0000
15.750 1.0399 0.07123 0.06310 0.0444 0.0829 1.0000
16.000 1.0372 0.07467 0.06663 0.0434 0.0813 1.0000
16.250 1.0379 0.07767 0.06965 0.0425 0.0799 1.0000
16.500 1.0387 0.08069 0.07269 0.0417 0.0786 1.0000
16.750 1.0199 0.08689 0.07917 0.0389 0.0774 1.0000
17.000 0.9986 0.09375 0.08626 0.0356 0.0761 1.0000
17.250 0.9731 0.10160 0.09434 0.0316 0.0749 1.0000
17.500 0.9390 0.11140 0.10436 0.0263 0.0738 1.0000
17.750 0.8970 0.12325 0.11642 0.0197 0.0725 1.0000
18.000 0.9408 0.11831 0.11129 0.0232 0.0715 1.0000
18.250 0.7336 0.17092 0.16440 -0.0058 0.0645 1.0000
18.500 0.7074 0.18394 0.17744 -0.0129 0.0617 1.0000
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