NACA 66-021 AIRFOIL (n66021-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-021 AIRFOIL (n66021-il) Reynolds number: 200,000 Max Cl/Cd: 25.48 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n66021-il-200000.txt Download as CSV file: xf-n66021-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-021 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.3077 0.15583 0.15234 -0.0473 0.9005 0.0734
-18.000 -0.3441 0.15018 0.14672 -0.0540 0.9014 0.0776
-17.750 -0.7034 0.10512 0.10105 -0.0816 1.0000 0.0463
-17.500 -0.6322 0.11177 0.10796 -0.0786 0.9807 0.0476
-17.250 -0.7330 0.09192 0.08754 -0.0892 0.9756 0.0442
-17.000 -0.7596 0.08427 0.07963 -0.0932 0.9694 0.0434
-16.750 -0.7888 0.07713 0.07216 -0.0961 0.9637 0.0426
-16.500 -0.8273 0.06980 0.06436 -0.0973 0.9581 0.0415
-16.250 -0.8837 0.06339 0.05728 -0.0958 0.9505 0.0405
-16.000 -0.9086 0.06094 0.05443 -0.0939 0.9425 0.0399
-15.750 -0.9040 0.05823 0.05151 -0.0933 0.9360 0.0398
-15.500 -0.9021 0.05561 0.04866 -0.0924 0.9303 0.0397
-15.250 -0.9005 0.05328 0.04609 -0.0911 0.9244 0.0398
-15.000 -0.8988 0.05128 0.04383 -0.0895 0.9191 0.0398
-14.750 -0.8793 0.04896 0.04132 -0.0896 0.9150 0.0401
-14.500 -0.8512 0.04712 0.03937 -0.0903 0.9108 0.0404
-14.250 -0.8236 0.04572 0.03790 -0.0907 0.9068 0.0409
-14.000 -0.8015 0.04463 0.03674 -0.0906 0.9031 0.0418
-13.750 -0.7798 0.04362 0.03565 -0.0906 0.8997 0.0427
-13.500 -0.7578 0.04260 0.03453 -0.0907 0.8962 0.0436
-13.250 -0.7343 0.04168 0.03348 -0.0907 0.8930 0.0445
-13.000 -0.7133 0.04084 0.03247 -0.0903 0.8899 0.0454
-12.750 -0.6773 0.04037 0.03204 -0.0911 0.8877 0.0466
-12.500 -0.6533 0.03986 0.03157 -0.0909 0.8853 0.0482
-12.250 -0.6318 0.03924 0.03095 -0.0908 0.8828 0.0497
-12.000 -0.6121 0.03856 0.03021 -0.0906 0.8802 0.0515
-11.750 -0.5943 0.03780 0.02949 -0.0901 0.8776 0.0538
-11.500 -0.5797 0.03700 0.02872 -0.0894 0.8750 0.0561
-11.250 -0.5653 0.03624 0.02788 -0.0886 0.8726 0.0593
-11.000 -0.5556 0.03523 0.02692 -0.0873 0.8704 0.0622
-10.750 -0.5448 0.03435 0.02602 -0.0860 0.8685 0.0665
-10.500 -0.5371 0.03333 0.02502 -0.0846 0.8665 0.0709
-10.250 -0.5263 0.03238 0.02407 -0.0836 0.8644 0.0778
-10.000 -0.5218 0.03112 0.02292 -0.0820 0.8620 0.0897
-9.750 -0.5221 0.02969 0.02174 -0.0796 0.8593 0.1167
-9.500 -0.5349 0.02774 0.02035 -0.0759 0.8568 0.1928
-9.250 -0.5503 0.02593 0.01903 -0.0716 0.8544 0.2730
-9.000 -0.5628 0.02448 0.01794 -0.0672 0.8523 0.3350
-8.750 -0.5744 0.02329 0.01710 -0.0625 0.8505 0.3969
-8.500 -0.5771 0.02266 0.01686 -0.0584 0.8488 0.4617
-8.250 -0.5133 0.02526 0.01996 -0.0613 0.8483 0.5440
-8.000 -0.4669 0.02716 0.02187 -0.0630 0.8473 0.5696
-7.750 -0.4406 0.02798 0.02265 -0.0628 0.8459 0.5862
-6.750 -0.3221 0.03367 0.02809 -0.0619 0.8408 0.6330
-6.500 -0.2877 0.03472 0.02907 -0.0625 0.8394 0.6378
-6.250 -0.2457 0.03579 0.03005 -0.0643 0.8385 0.6399
-6.000 -0.2416 0.03588 0.03010 -0.0616 0.8370 0.6525
-5.750 -0.1992 0.03680 0.03095 -0.0636 0.8364 0.6540
-5.500 -0.1596 0.03761 0.03169 -0.0652 0.8358 0.6562
-5.250 -0.1598 0.03768 0.03174 -0.0619 0.8345 0.6690
-5.000 -0.1186 0.03838 0.03238 -0.0639 0.8340 0.6705
-4.750 -0.0803 0.03899 0.03293 -0.0656 0.8335 0.6726
-4.500 -0.0870 0.03909 0.03301 -0.0613 0.8324 0.6859
-4.250 -0.0453 0.03956 0.03344 -0.0634 0.8318 0.6873
-4.000 -0.0069 0.04003 0.03387 -0.0651 0.8311 0.6893
-3.750 0.0247 0.04060 0.03442 -0.0661 0.8305 0.6928
-3.500 0.0042 0.04173 0.03560 -0.0601 0.8287 0.7045
-3.250 -0.1488 0.04562 0.03969 -0.0303 0.8227 0.7208
-3.000 -0.1218 0.04633 0.04038 -0.0301 0.8213 0.7225
-2.750 -0.0911 0.04692 0.04096 -0.0307 0.8198 0.7249
-2.500 -0.0909 0.04775 0.04180 -0.0264 0.8187 0.7303
-2.250 -0.1004 0.04783 0.04186 -0.0208 0.8164 0.7405
-2.000 -0.1710 0.04834 0.04238 -0.0049 0.8149 0.7560
-1.750 -0.0889 0.04815 0.04213 -0.0147 0.8135 0.7565
-1.500 -0.0102 0.04791 0.04184 -0.0240 0.8128 0.7572
-1.250 0.0519 0.04791 0.04183 -0.0304 0.8117 0.7585
-0.250 -0.1639 0.04932 0.04330 0.0237 0.7861 0.7933
0.000 -0.1076 0.04954 0.04353 0.0182 0.7824 0.7941
0.250 -0.0444 0.04967 0.04365 0.0116 0.7798 0.7951
0.500 0.0254 0.04971 0.04371 0.0041 0.7779 0.7965
0.750 0.0950 0.04976 0.04377 -0.0034 0.7766 0.7986
1.000 0.1561 0.04968 0.04372 -0.0095 0.7755 0.8016
1.250 0.2052 0.04949 0.04355 -0.0136 0.7746 0.8052
1.500 0.0104 0.04793 0.04187 0.0239 0.7572 0.8129
1.750 0.0901 0.04817 0.04216 0.0145 0.7565 0.8136
2.000 0.1755 0.04840 0.04244 0.0042 0.7559 0.8150
2.250 0.3250 0.05211 0.04639 -0.0139 0.7564 0.8671
2.500 0.4047 0.05046 0.04482 -0.0238 0.7560 0.8685
2.750 0.0902 0.04690 0.04094 0.0309 0.7249 0.8198
3.000 0.1237 0.04633 0.04039 0.0298 0.7225 0.8213
3.250 0.1475 0.04558 0.03965 0.0305 0.7208 0.8227
3.500 -0.0044 0.04171 0.03558 0.0601 0.7045 0.8287
3.750 0.0281 0.04089 0.03476 0.0589 0.7030 0.8294
4.000 0.0067 0.04004 0.03387 0.0651 0.6893 0.8312
4.250 0.0454 0.03956 0.03343 0.0634 0.6873 0.8318
4.500 0.0870 0.03909 0.03301 0.0613 0.6859 0.8324
5.000 0.7949 0.03263 0.02747 -0.0396 0.7036 0.8638
5.250 0.1459 0.03794 0.03198 0.0637 0.6658 0.8347
5.500 0.1594 0.03762 0.03171 0.0652 0.6562 0.8358
5.750 0.1995 0.03679 0.03093 0.0635 0.6540 0.8364
6.000 0.2129 0.03655 0.03074 0.0650 0.6444 0.8376
6.250 0.2454 0.03582 0.03008 0.0643 0.6399 0.8384
6.500 0.2870 0.03477 0.02912 0.0626 0.6379 0.8394
6.750 0.3232 0.03359 0.02801 0.0617 0.6330 0.8407
7.500 0.4156 0.02890 0.02351 0.0624 0.5984 0.8445
7.750 0.4479 0.02764 0.02232 0.0620 0.5891 0.8458
8.000 0.4669 0.02716 0.02187 0.0630 0.5692 0.8474
8.250 0.5164 0.02509 0.01978 0.0610 0.5429 0.8483
8.500 0.5772 0.02265 0.01683 0.0584 0.4594 0.8488
8.750 0.5746 0.02329 0.01709 0.0624 0.3965 0.8504
9.000 0.5631 0.02447 0.01793 0.0672 0.3346 0.8523
9.250 0.5492 0.02598 0.01905 0.0717 0.2688 0.8545
9.500 0.5353 0.02773 0.02034 0.0758 0.1923 0.8568
9.750 0.5229 0.02966 0.02172 0.0795 0.1172 0.8594
10.000 0.5219 0.03113 0.02292 0.0819 0.0891 0.8620
10.250 0.5278 0.03230 0.02400 0.0834 0.0781 0.8645
10.500 0.5378 0.03330 0.02498 0.0845 0.0707 0.8666
10.750 0.5456 0.03432 0.02599 0.0859 0.0660 0.8685
11.000 0.5562 0.03520 0.02689 0.0872 0.0618 0.8705
11.250 0.5660 0.03622 0.02786 0.0885 0.0593 0.8726
11.500 0.5807 0.03696 0.02867 0.0893 0.0563 0.8751
11.750 0.5951 0.03777 0.02945 0.0900 0.0537 0.8776
12.000 0.6129 0.03853 0.03017 0.0905 0.0515 0.8802
12.250 0.6323 0.03923 0.03093 0.0907 0.0494 0.8830
12.500 0.6544 0.03982 0.03153 0.0908 0.0481 0.8854
12.750 0.6777 0.04033 0.03202 0.0910 0.0469 0.8878
13.000 0.7154 0.04077 0.03238 0.0901 0.0455 0.8900
13.250 0.7369 0.04163 0.03342 0.0904 0.0446 0.8930
13.500 0.7599 0.04258 0.03451 0.0905 0.0436 0.8963
13.750 0.7800 0.04357 0.03560 0.0905 0.0426 0.8999
14.000 0.8025 0.04459 0.03669 0.0905 0.0418 0.9033
14.250 0.8232 0.04566 0.03784 0.0907 0.0410 0.9070
14.500 0.8518 0.04708 0.03933 0.0902 0.0404 0.9109
14.750 0.8847 0.04914 0.04149 0.0890 0.0400 0.9149
15.000 0.8976 0.05126 0.04382 0.0896 0.0398 0.9194
15.250 0.9046 0.05338 0.04617 0.0907 0.0398 0.9245
15.500 0.9044 0.05566 0.04870 0.0921 0.0398 0.9306
15.750 0.9082 0.05819 0.05145 0.0930 0.0398 0.9362
16.000 0.9076 0.06068 0.05418 0.0939 0.0400 0.9433
16.250 0.8982 0.06347 0.05726 0.0948 0.0401 0.9504
16.500 0.8327 0.06961 0.06414 0.0969 0.0413 0.9588
16.750 0.7937 0.07684 0.07185 0.0956 0.0422 0.9644
17.000 0.7619 0.08440 0.07976 0.0927 0.0435 0.9701
17.250 0.7386 0.09170 0.08731 0.0888 0.0443 0.9766
17.500 0.7202 0.09872 0.09452 0.0845 0.0449 0.9884
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