NACA 0021 (naca0021-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0021 (naca0021-il) Reynolds number: 100,000 Max Cl/Cd: 36.59 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0021-il-100000.txt Download as CSV file: xf-naca0021-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0021
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.5418 0.17959 0.17300 -0.0051 1.0000 0.1943
-16.000 -0.5218 0.17458 0.16798 -0.0056 1.0000 0.1957
-15.750 -1.0757 0.06945 0.06174 -0.0558 1.0000 0.1532
-15.000 -1.0716 0.06221 0.05443 -0.0551 1.0000 0.1626
-14.750 -1.1181 0.05655 0.04843 -0.0539 1.0000 0.1642
-14.500 -1.1584 0.05230 0.04383 -0.0512 1.0000 0.1659
-14.250 -1.1225 0.05198 0.04374 -0.0516 1.0000 0.1705
-14.000 -1.1217 0.05028 0.04198 -0.0501 1.0000 0.1742
-13.750 -1.1410 0.04769 0.03917 -0.0471 1.0000 0.1773
-13.500 -1.1689 0.04524 0.03640 -0.0425 1.0000 0.1797
-13.250 -1.1295 0.04478 0.03622 -0.0438 1.0000 0.1853
-13.000 -1.1311 0.04343 0.03479 -0.0411 1.0000 0.1894
-12.750 -1.1495 0.04176 0.03290 -0.0361 1.0000 0.1928
-12.500 -1.1393 0.04058 0.03175 -0.0342 1.0000 0.1974
-12.250 -1.1243 0.03993 0.03119 -0.0327 1.0000 0.2025
-12.000 -1.1374 0.03889 0.03002 -0.0271 1.0000 0.2064
-11.750 -1.1599 0.03782 0.02870 -0.0199 1.0000 0.2097
-11.500 -1.1248 0.03722 0.02841 -0.0211 1.0000 0.2162
-11.250 -1.1280 0.03641 0.02754 -0.0166 1.0000 0.2212
-11.000 -1.1446 0.03548 0.02634 -0.0100 1.0000 0.2255
-10.750 -1.1160 0.03489 0.02605 -0.0102 1.0000 0.2321
-10.500 -1.1166 0.03422 0.02531 -0.0059 1.0000 0.2379
-10.250 -1.1202 0.03336 0.02431 -0.0011 1.0000 0.2434
-10.000 -1.1022 0.03292 0.02408 0.0004 1.0000 0.2500
-9.750 -1.1033 0.03226 0.02330 0.0049 1.0000 0.2565
-9.500 -1.0943 0.03159 0.02268 0.0077 1.0000 0.2630
-9.250 -1.0843 0.03117 0.02232 0.0105 1.0000 0.2701
-9.000 -1.0869 0.03049 0.02143 0.0152 1.0000 0.2772
-8.750 -1.0682 0.03009 0.02126 0.0165 1.0000 0.2846
-8.500 -1.0638 0.02958 0.02066 0.0201 1.0000 0.2927
-8.250 -1.0510 0.02910 0.02027 0.0223 1.0000 0.3003
-8.000 -1.0410 0.02874 0.01992 0.0250 1.0000 0.3089
-7.750 -1.0310 0.02826 0.01942 0.0276 1.0000 0.3173
-7.500 -1.0177 0.02799 0.01923 0.0297 1.0000 0.3261
-7.250 -1.0080 0.02755 0.01873 0.0322 1.0000 0.3354
-7.000 -0.9930 0.02735 0.01865 0.0340 1.0000 0.3444
-6.750 -0.9825 0.02698 0.01820 0.0363 1.0000 0.3544
-6.500 -0.9668 0.02682 0.01818 0.0379 1.0000 0.3638
-6.250 -0.9284 0.02666 0.01804 0.0351 0.9937 0.3776
-6.000 -0.8880 0.02654 0.01784 0.0320 0.9848 0.3929
-5.750 -0.8396 0.02658 0.01805 0.0277 0.9774 0.4074
-5.500 -0.8021 0.02640 0.01794 0.0254 0.9671 0.4209
-5.250 -0.7628 0.02623 0.01776 0.0227 0.9576 0.4362
-5.000 -0.7209 0.02613 0.01771 0.0198 0.9483 0.4515
-4.750 -0.6844 0.02600 0.01771 0.0180 0.9377 0.4647
-4.500 -0.6395 0.02580 0.01754 0.0147 0.9295 0.4805
-4.250 -0.6102 0.02564 0.01736 0.0142 0.9173 0.4952
-4.000 -0.5600 0.02548 0.01736 0.0103 0.9104 0.5102
-3.750 -0.5318 0.02530 0.01722 0.0102 0.8979 0.5237
-3.500 -0.4845 0.02500 0.01692 0.0068 0.8909 0.5408
-3.250 -0.4524 0.02493 0.01698 0.0063 0.8789 0.5538
-3.000 -0.4038 0.02461 0.01674 0.0029 0.8719 0.5695
-2.750 -0.3715 0.02434 0.01647 0.0024 0.8613 0.5850
-2.500 -0.3309 0.02410 0.01632 0.0008 0.8520 0.5996
-2.250 -0.2802 0.02367 0.01597 -0.0024 0.8468 0.6147
-2.000 -0.2618 0.02352 0.01582 -0.0004 0.8315 0.6290
-1.750 -0.2139 0.02312 0.01549 -0.0028 0.8255 0.6439
-1.500 -0.1906 0.02308 0.01553 -0.0014 0.8104 0.6565
-1.250 -0.1507 0.02259 0.01501 -0.0025 0.8034 0.6726
-0.750 -0.0906 0.02245 0.01497 -0.0015 0.7776 0.6986
-0.500 -0.0653 0.02229 0.01480 -0.0003 0.7643 0.7139
-0.250 -0.0304 0.02238 0.01495 -0.0005 0.7513 0.7249
0.000 0.0000 0.02216 0.01468 0.0000 0.7398 0.7398
0.250 0.0304 0.02238 0.01495 0.0005 0.7249 0.7513
0.500 0.0653 0.02229 0.01480 0.0003 0.7139 0.7643
0.750 0.0906 0.02245 0.01496 0.0015 0.6986 0.7776
1.250 0.1507 0.02260 0.01501 0.0025 0.6726 0.8034
1.500 0.1906 0.02308 0.01553 0.0014 0.6565 0.8104
1.750 0.2139 0.02312 0.01549 0.0028 0.6439 0.8255
2.000 0.2618 0.02352 0.01582 0.0004 0.6290 0.8315
2.250 0.2802 0.02366 0.01597 0.0024 0.6147 0.8468
2.500 0.3309 0.02410 0.01632 -0.0008 0.5996 0.8520
2.750 0.3713 0.02434 0.01646 -0.0024 0.5850 0.8614
3.000 0.4037 0.02461 0.01674 -0.0029 0.5695 0.8719
3.250 0.4523 0.02492 0.01698 -0.0063 0.5538 0.8789
3.500 0.4844 0.02500 0.01692 -0.0067 0.5408 0.8909
3.750 0.5316 0.02530 0.01722 -0.0102 0.5237 0.8979
4.000 0.5600 0.02548 0.01735 -0.0103 0.5102 0.9105
4.250 0.6101 0.02563 0.01735 -0.0142 0.4952 0.9174
4.500 0.6395 0.02580 0.01754 -0.0147 0.4805 0.9296
4.750 0.6843 0.02599 0.01771 -0.0180 0.4647 0.9378
5.000 0.7209 0.02612 0.01770 -0.0198 0.4515 0.9484
5.250 0.7627 0.02622 0.01775 -0.0227 0.4362 0.9578
5.500 0.8021 0.02639 0.01793 -0.0254 0.4210 0.9672
5.750 0.8394 0.02657 0.01804 -0.0277 0.4075 0.9776
6.000 0.8879 0.02653 0.01783 -0.0320 0.3929 0.9849
6.250 0.9285 0.02665 0.01803 -0.0351 0.3776 0.9938
6.500 0.9665 0.02681 0.01817 -0.0379 0.3639 1.0000
6.750 0.9822 0.02697 0.01819 -0.0363 0.3545 1.0000
7.000 0.9927 0.02734 0.01864 -0.0340 0.3445 1.0000
7.250 1.0077 0.02754 0.01872 -0.0322 0.3354 1.0000
7.500 1.0174 0.02798 0.01922 -0.0296 0.3261 1.0000
7.750 1.0308 0.02825 0.01941 -0.0275 0.3173 1.0000
8.000 1.0408 0.02873 0.01991 -0.0250 0.3089 1.0000
8.250 1.0508 0.02909 0.02026 -0.0223 0.3003 1.0000
8.500 1.0636 0.02957 0.02064 -0.0201 0.2927 1.0000
8.750 1.0680 0.03008 0.02125 -0.0165 0.2846 1.0000
9.000 1.0866 0.03048 0.02142 -0.0151 0.2772 1.0000
9.250 1.0841 0.03116 0.02231 -0.0105 0.2701 1.0000
9.500 1.0941 0.03159 0.02267 -0.0077 0.2630 1.0000
9.750 1.1032 0.03225 0.02329 -0.0048 0.2565 1.0000
10.000 1.1020 0.03291 0.02406 -0.0004 0.2500 1.0000
10.250 1.1200 0.03335 0.02430 0.0012 0.2434 1.0000
10.500 1.1165 0.03421 0.02530 0.0059 0.2379 1.0000
10.750 1.1160 0.03488 0.02604 0.0102 0.2321 1.0000
11.000 1.1445 0.03547 0.02633 0.0100 0.2255 1.0000
11.250 1.1281 0.03640 0.02753 0.0166 0.2212 1.0000
11.500 1.1251 0.03721 0.02840 0.0211 0.2162 1.0000
11.750 1.1600 0.03781 0.02869 0.0199 0.2097 1.0000
12.000 1.1377 0.03888 0.03001 0.0271 0.2064 1.0000
12.250 1.1248 0.03992 0.03118 0.0326 0.2024 1.0000
12.500 1.1405 0.04056 0.03173 0.0341 0.1973 1.0000
12.750 1.1499 0.04176 0.03290 0.0360 0.1927 1.0000
13.000 1.1318 0.04342 0.03479 0.0410 0.1893 1.0000
13.250 1.1308 0.04476 0.03620 0.0436 0.1852 1.0000
13.500 1.1694 0.04524 0.03641 0.0424 0.1797 1.0000
13.750 1.1418 0.04770 0.03918 0.0470 0.1772 1.0000
14.000 1.1230 0.05026 0.04196 0.0499 0.1741 1.0000
14.250 1.1250 0.05190 0.04364 0.0513 0.1704 1.0000
14.500 1.1589 0.05233 0.04386 0.0510 0.1658 1.0000
14.750 1.1189 0.05658 0.04847 0.0537 0.1641 1.0000
15.000 1.0729 0.06222 0.05445 0.0549 0.1625 1.0000
15.250 0.5376 0.16648 0.15990 0.0110 0.2097 1.0000
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