NACA 0021 (naca0021-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0021 (naca0021-il) Reynolds number: 100,000 Max Cl/Cd: 35.6 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0021-il-100000-n5.txt Download as CSV file: xf-naca0021-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9402 0.10752 0.09991 -0.0370 1.0000 0.1018
-17.750 -0.9328 0.10538 0.09779 -0.0377 1.0000 0.1038
-17.500 -0.9578 0.09795 0.09019 -0.0412 1.0000 0.1062
-17.250 -0.9909 0.08952 0.08148 -0.0450 1.0000 0.1087
-17.000 -0.9992 0.08512 0.07699 -0.0466 1.0000 0.1109
-16.750 -0.9955 0.08260 0.07448 -0.0473 1.0000 0.1131
-16.500 -1.0025 0.07853 0.07032 -0.0486 1.0000 0.1156
-16.250 -1.0153 0.07374 0.06534 -0.0502 1.0000 0.1183
-16.000 -1.0195 0.07026 0.06176 -0.0511 1.0000 0.1207
-15.750 -1.0163 0.06785 0.05937 -0.0515 1.0000 0.1232
-15.500 -1.0189 0.06474 0.05618 -0.0521 1.0000 0.1261
-15.250 -1.0251 0.06123 0.05251 -0.0528 1.0000 0.1291
-15.000 -1.0233 0.05880 0.05005 -0.0529 1.0000 0.1319
-14.750 -1.0209 0.05655 0.04779 -0.0529 1.0000 0.1348
-14.500 -1.0214 0.05400 0.04515 -0.0530 1.0000 0.1381
-14.250 -1.0237 0.05130 0.04227 -0.0529 1.0000 0.1417
-14.000 -1.0175 0.04963 0.04067 -0.0524 1.0000 0.1447
-13.750 -1.0148 0.04765 0.03865 -0.0519 1.0000 0.1482
-13.500 -1.0133 0.04558 0.03646 -0.0514 1.0000 0.1522
-13.250 -1.0085 0.04391 0.03477 -0.0506 1.0000 0.1558
-13.000 -1.0040 0.04231 0.03317 -0.0497 1.0000 0.1595
-12.750 -1.0002 0.04067 0.03145 -0.0486 1.0000 0.1639
-12.500 -0.9950 0.03921 0.02996 -0.0474 1.0000 0.1681
-12.250 -0.9897 0.03791 0.02868 -0.0460 1.0000 0.1722
-12.000 -0.9848 0.03661 0.02731 -0.0445 1.0000 0.1770
-11.750 -0.9793 0.03543 0.02609 -0.0427 1.0000 0.1817
-11.500 -0.9744 0.03437 0.02508 -0.0407 1.0000 0.1861
-11.250 -0.9701 0.03337 0.02402 -0.0385 1.0000 0.1912
-11.000 -0.9657 0.03245 0.02309 -0.0360 1.0000 0.1962
-10.750 -0.9631 0.03164 0.02232 -0.0330 1.0000 0.2008
-10.500 -0.9614 0.03091 0.02155 -0.0297 1.0000 0.2062
-10.250 -0.9600 0.03024 0.02087 -0.0262 1.0000 0.2113
-10.000 -0.9613 0.02966 0.02035 -0.0221 1.0000 0.2159
-9.750 -0.9641 0.02916 0.01983 -0.0176 1.0000 0.2211
-9.500 -0.9682 0.02873 0.01935 -0.0127 1.0000 0.2262
-9.250 -0.9754 0.02836 0.01905 -0.0071 1.0000 0.2304
-9.000 -0.9797 0.02800 0.01870 -0.0020 1.0000 0.2355
-8.750 -0.9798 0.02764 0.01827 0.0023 1.0000 0.2416
-8.500 -0.9662 0.02715 0.01787 0.0041 0.9973 0.2483
-8.250 -0.9335 0.02663 0.01727 0.0022 0.9916 0.2585
-8.000 -0.9040 0.02607 0.01679 0.0011 0.9844 0.2674
-7.750 -0.8699 0.02558 0.01625 -0.0009 0.9784 0.2782
-7.500 -0.8414 0.02509 0.01582 -0.0016 0.9702 0.2878
-7.250 -0.8072 0.02462 0.01535 -0.0035 0.9640 0.2987
-7.000 -0.7788 0.02420 0.01494 -0.0041 0.9554 0.3093
-6.750 -0.7451 0.02376 0.01455 -0.0056 0.9487 0.3201
-6.500 -0.7144 0.02337 0.01412 -0.0066 0.9409 0.3319
-6.250 -0.6831 0.02297 0.01380 -0.0075 0.9329 0.3426
-6.000 -0.6474 0.02256 0.01338 -0.0093 0.9270 0.3549
-5.750 -0.6236 0.02224 0.01310 -0.0086 0.9157 0.3654
-5.500 -0.5883 0.02183 0.01272 -0.0101 0.9093 0.3774
-5.250 -0.5654 0.02155 0.01244 -0.0092 0.8974 0.3886
-5.000 -0.5319 0.02118 0.01212 -0.0102 0.8900 0.4002
-4.750 -0.5085 0.02092 0.01182 -0.0094 0.8780 0.4120
-4.500 -0.4764 0.02057 0.01155 -0.0100 0.8698 0.4233
-4.250 -0.4526 0.02033 0.01129 -0.0091 0.8575 0.4350
-4.000 -0.4218 0.02001 0.01103 -0.0094 0.8485 0.4468
-3.750 -0.3976 0.01980 0.01082 -0.0086 0.8358 0.4583
-3.500 -0.3676 0.01951 0.01054 -0.0087 0.8263 0.4709
-3.250 -0.3435 0.01933 0.01040 -0.0077 0.8129 0.4821
-3.000 -0.3136 0.01906 0.01008 -0.0078 0.8032 0.4954
-2.750 -0.2897 0.01892 0.01002 -0.0068 0.7890 0.5063
-2.500 -0.2623 0.01872 0.00978 -0.0064 0.7775 0.5194
-2.250 -0.2360 0.01857 0.00968 -0.0058 0.7643 0.5311
-2.000 -0.2100 0.01842 0.00953 -0.0051 0.7513 0.5436
-1.750 -0.1825 0.01828 0.00937 -0.0047 0.7392 0.5565
-1.500 -0.1573 0.01819 0.00932 -0.0039 0.7251 0.5685
-1.250 -0.1306 0.01807 0.00914 -0.0033 0.7130 0.5823
-1.000 -0.1044 0.01802 0.00915 -0.0027 0.6989 0.5940
-0.750 -0.0788 0.01795 0.00906 -0.0019 0.6858 0.6074
-0.500 -0.0516 0.01791 0.00901 -0.0014 0.6731 0.6202
-0.250 -0.0263 0.01789 0.00903 -0.0006 0.6591 0.6329
0.000 0.0000 0.01787 0.00894 0.0000 0.6469 0.6469
0.250 0.0263 0.01789 0.00903 0.0006 0.6329 0.6591
0.500 0.0516 0.01791 0.00901 0.0014 0.6202 0.6731
0.750 0.0788 0.01795 0.00906 0.0019 0.6074 0.6858
1.000 0.1044 0.01802 0.00915 0.0027 0.5940 0.6989
1.250 0.1306 0.01807 0.00914 0.0033 0.5823 0.7130
1.500 0.1573 0.01819 0.00932 0.0039 0.5685 0.7251
1.750 0.1825 0.01828 0.00937 0.0047 0.5565 0.7392
2.000 0.2100 0.01842 0.00953 0.0051 0.5436 0.7514
2.250 0.2360 0.01857 0.00968 0.0058 0.5311 0.7643
2.500 0.2623 0.01872 0.00977 0.0064 0.5194 0.7775
2.750 0.2897 0.01892 0.01002 0.0068 0.5064 0.7890
3.000 0.3136 0.01906 0.01008 0.0078 0.4954 0.8032
3.250 0.3435 0.01933 0.01040 0.0077 0.4821 0.8129
3.500 0.3676 0.01951 0.01054 0.0087 0.4709 0.8263
3.750 0.3976 0.01980 0.01082 0.0086 0.4583 0.8358
4.000 0.4218 0.02001 0.01103 0.0094 0.4468 0.8485
4.250 0.4526 0.02033 0.01129 0.0091 0.4350 0.8576
4.500 0.4764 0.02057 0.01155 0.0100 0.4233 0.8698
4.750 0.5085 0.02091 0.01182 0.0094 0.4120 0.8781
5.000 0.5319 0.02117 0.01211 0.0102 0.4002 0.8901
5.250 0.5654 0.02155 0.01244 0.0092 0.3886 0.8974
5.500 0.5884 0.02183 0.01272 0.0101 0.3774 0.9094
5.750 0.6236 0.02223 0.01310 0.0086 0.3654 0.9157
6.000 0.6472 0.02255 0.01337 0.0093 0.3549 0.9271
6.250 0.6832 0.02297 0.01380 0.0075 0.3426 0.9329
6.500 0.7144 0.02337 0.01411 0.0066 0.3319 0.9410
6.750 0.7453 0.02376 0.01454 0.0056 0.3201 0.9488
7.000 0.7789 0.02419 0.01493 0.0040 0.3093 0.9555
7.250 0.8074 0.02462 0.01535 0.0034 0.2987 0.9640
7.500 0.8416 0.02508 0.01582 0.0016 0.2878 0.9703
7.750 0.8702 0.02558 0.01624 0.0008 0.2782 0.9785
8.000 0.9042 0.02607 0.01678 -0.0011 0.2674 0.9845
8.250 0.9338 0.02662 0.01726 -0.0023 0.2585 0.9916
8.500 0.9666 0.02715 0.01786 -0.0041 0.2482 0.9974
8.750 0.9798 0.02763 0.01825 -0.0023 0.2417 1.0000
9.000 0.9797 0.02799 0.01869 0.0020 0.2355 1.0000
9.250 0.9755 0.02835 0.01904 0.0071 0.2303 1.0000
9.500 0.9684 0.02872 0.01934 0.0126 0.2262 1.0000
9.750 0.9643 0.02915 0.01981 0.0176 0.2211 1.0000
10.000 0.9615 0.02964 0.02033 0.0221 0.2159 1.0000
10.250 0.9603 0.03022 0.02085 0.0262 0.2113 1.0000
10.500 0.9617 0.03089 0.02153 0.0297 0.2061 1.0000
10.750 0.9636 0.03163 0.02230 0.0329 0.2008 1.0000
11.000 0.9662 0.03243 0.02306 0.0359 0.1962 1.0000
11.250 0.9707 0.03335 0.02400 0.0384 0.1912 1.0000
11.500 0.9752 0.03435 0.02505 0.0406 0.1860 1.0000
11.750 0.9802 0.03541 0.02607 0.0426 0.1816 1.0000
12.000 0.9858 0.03659 0.02729 0.0443 0.1769 1.0000
12.250 0.9907 0.03788 0.02865 0.0459 0.1721 1.0000
12.500 0.9962 0.03918 0.02992 0.0473 0.1681 1.0000
12.750 1.0014 0.04064 0.03143 0.0485 0.1638 1.0000
13.000 1.0053 0.04227 0.03314 0.0495 0.1594 1.0000
13.250 1.0100 0.04387 0.03473 0.0504 0.1557 1.0000
13.500 1.0148 0.04556 0.03643 0.0512 0.1521 1.0000
13.750 1.0165 0.04762 0.03861 0.0517 0.1481 1.0000
14.000 1.0193 0.04959 0.04062 0.0522 0.1446 1.0000
14.250 1.0255 0.05126 0.04223 0.0526 0.1416 1.0000
14.500 1.0232 0.05397 0.04511 0.0527 0.1380 1.0000
14.750 1.0229 0.05650 0.04773 0.0527 0.1347 1.0000
15.000 1.0257 0.05872 0.04996 0.0527 0.1318 1.0000
15.250 1.0271 0.06121 0.05248 0.0525 0.1290 1.0000
15.500 1.0212 0.06468 0.05612 0.0518 0.1259 1.0000
15.750 1.0190 0.06776 0.05927 0.0512 0.1231 1.0000
16.000 1.0225 0.07012 0.06162 0.0509 0.1206 1.0000
16.250 1.0175 0.07372 0.06532 0.0499 0.1182 1.0000
16.500 1.0052 0.07846 0.07025 0.0483 0.1155 1.0000
16.750 0.9987 0.08245 0.07433 0.0470 0.1130 1.0000
17.000 1.0031 0.08489 0.07674 0.0463 0.1108 1.0000
17.250 0.9931 0.08956 0.08152 0.0446 0.1086 1.0000
17.500 0.9608 0.09786 0.09011 0.0408 0.1061 1.0000
17.750 0.9377 0.10500 0.09740 0.0375 0.1037 1.0000
18.000 0.9457 0.10705 0.09942 0.0368 0.1018 1.0000
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