NACA 23021 (naca23021-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23021 (naca23021-il) Reynolds number: 100,000 Max Cl/Cd: 36.96 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23021-il-100000.txt Download as CSV file: xf-naca23021-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23021
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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.5131 0.18179 0.17550 -0.0077 1.0000 0.1682
-17.000 -0.4844 0.17781 0.17151 -0.0068 1.0000 0.1700
-16.750 -1.0007 0.07755 0.06997 -0.0654 1.0000 0.1094
-16.500 -1.0141 0.07306 0.06537 -0.0659 1.0000 0.1103
-16.250 -0.9702 0.07357 0.06609 -0.0648 1.0000 0.1129
-16.000 -1.0094 0.06748 0.05971 -0.0656 1.0000 0.1130
-15.750 -1.0276 0.06352 0.05555 -0.0653 1.0000 0.1139
-15.500 -1.0433 0.06003 0.05186 -0.0645 1.0000 0.1149
-15.250 -1.0584 0.05687 0.04848 -0.0632 1.0000 0.1160
-15.000 -1.0737 0.05400 0.04536 -0.0612 1.0000 0.1173
-14.750 -1.0894 0.05144 0.04253 -0.0586 1.0000 0.1184
-14.500 -1.1063 0.04925 0.04004 -0.0552 1.0000 0.1195
-14.250 -1.0696 0.04762 0.03860 -0.0562 1.0000 0.1227
-14.000 -1.0594 0.04605 0.03700 -0.0548 1.0000 0.1251
-13.750 -1.0566 0.04441 0.03521 -0.0526 1.0000 0.1276
-13.500 -1.0610 0.04281 0.03339 -0.0494 1.0000 0.1298
-13.250 -1.0323 0.04133 0.03204 -0.0496 1.0000 0.1336
-13.000 -1.0169 0.04013 0.03087 -0.0483 1.0000 0.1373
-12.750 -1.0147 0.03882 0.02941 -0.0454 1.0000 0.1407
-12.500 -0.9922 0.03754 0.02824 -0.0448 1.0000 0.1455
-12.250 -0.9803 0.03650 0.02726 -0.0428 1.0000 0.1504
-12.000 -0.9815 0.03541 0.02601 -0.0390 1.0000 0.1549
-11.750 -0.9599 0.03438 0.02526 -0.0382 1.0000 0.1616
-11.500 -0.9630 0.03346 0.02420 -0.0339 1.0000 0.1674
-11.250 -0.9518 0.03253 0.02353 -0.0316 1.0000 0.1749
-11.000 -0.9566 0.03173 0.02269 -0.0267 1.0000 0.1821
-10.750 -0.9574 0.03102 0.02217 -0.0224 1.0000 0.1897
-10.500 -0.9662 0.03039 0.02154 -0.0166 1.0000 0.1975
-10.250 -0.9724 0.02980 0.02108 -0.0113 1.0000 0.2060
-10.000 -0.9773 0.02916 0.02053 -0.0062 1.0000 0.2158
-9.750 -0.9832 0.02860 0.01996 -0.0009 1.0000 0.2273
-9.500 -0.9856 0.02806 0.01959 0.0038 1.0000 0.2389
-9.250 -0.9874 0.02756 0.01920 0.0084 1.0000 0.2521
-9.000 -0.9878 0.02710 0.01882 0.0128 1.0000 0.2671
-8.750 -0.9866 0.02668 0.01847 0.0169 1.0000 0.2835
-8.500 -0.9837 0.02632 0.01816 0.0207 1.0000 0.3009
-8.250 -0.9791 0.02601 0.01787 0.0241 1.0000 0.3186
-8.000 -0.9725 0.02578 0.01765 0.0273 1.0000 0.3359
-7.750 -0.9627 0.02560 0.01761 0.0299 1.0000 0.3519
-7.500 -0.9240 0.02562 0.01763 0.0273 0.9928 0.3748
-7.250 -0.8839 0.02567 0.01772 0.0245 0.9836 0.3956
-7.000 -0.8416 0.02583 0.01792 0.0215 0.9749 0.4164
-6.750 -0.8015 0.02597 0.01814 0.0191 0.9649 0.4357
-6.500 -0.7634 0.02609 0.01835 0.0172 0.9547 0.4527
-6.250 -0.7179 0.02611 0.01842 0.0139 0.9462 0.4692
-6.000 -0.6878 0.02594 0.01818 0.0133 0.9345 0.4834
-5.750 -0.6384 0.02589 0.01820 0.0095 0.9274 0.4982
-5.500 -0.6093 0.02575 0.01809 0.0093 0.9152 0.5099
-5.250 -0.5629 0.02552 0.01779 0.0060 0.9082 0.5262
-5.000 -0.5327 0.02555 0.01797 0.0060 0.8958 0.5391
-4.750 -0.4841 0.02543 0.01791 0.0028 0.8889 0.5564
-4.500 -0.4563 0.02527 0.01772 0.0030 0.8770 0.5719
-4.250 -0.4080 0.02506 0.01761 0.0001 0.8695 0.5867
-4.000 -0.3548 0.02463 0.01723 -0.0037 0.8647 0.6010
-3.750 -0.3387 0.02440 0.01691 -0.0014 0.8493 0.6152
-3.500 -0.2849 0.02404 0.01668 -0.0048 0.8438 0.6279
-3.250 -0.2638 0.02383 0.01647 -0.0032 0.8292 0.6414
-3.000 -0.2184 0.02341 0.01607 -0.0051 0.8221 0.6559
-2.750 -0.1920 0.02331 0.01602 -0.0041 0.8076 0.6680
-2.500 -0.1552 0.02275 0.01538 -0.0046 0.7991 0.6840
-2.250 -0.1238 0.02279 0.01552 -0.0041 0.7837 0.6945
-2.000 -0.0908 0.02239 0.01506 -0.0040 0.7729 0.7091
-1.750 -0.0587 0.02238 0.01507 -0.0036 0.7580 0.7205
-1.500 -0.0318 0.02226 0.01493 -0.0026 0.7438 0.7335
-1.250 0.0055 0.02216 0.01477 -0.0030 0.7317 0.7456
-1.000 0.0307 0.02225 0.01486 -0.0018 0.7156 0.7574
-0.750 0.0619 0.02228 0.01483 -0.0014 0.7019 0.7695
-0.500 0.0951 0.02233 0.01482 -0.0014 0.6876 0.7801
-0.250 0.1219 0.02253 0.01500 -0.0005 0.6719 0.7922
0.000 0.1570 0.02266 0.01504 -0.0008 0.6582 0.8022
0.250 0.1900 0.02288 0.01521 -0.0008 0.6428 0.8126
0.500 0.2180 0.02307 0.01537 -0.0003 0.6275 0.8237
0.750 0.2593 0.02338 0.01557 -0.0017 0.6131 0.8321
1.000 0.2855 0.02350 0.01563 -0.0009 0.5982 0.8447
1.250 0.3290 0.02395 0.01604 -0.0030 0.5816 0.8518
1.500 0.3560 0.02406 0.01602 -0.0024 0.5687 0.8654
1.750 0.4079 0.02447 0.01633 -0.0061 0.5517 0.8710
2.000 0.4293 0.02467 0.01653 -0.0048 0.5371 0.8858
2.250 0.4848 0.02502 0.01678 -0.0096 0.5203 0.8906
2.750 0.5612 0.02544 0.01703 -0.0133 0.4905 0.9102
3.000 0.6017 0.02568 0.01721 -0.0157 0.4753 0.9192
3.250 0.6386 0.02580 0.01713 -0.0175 0.4621 0.9293
3.500 0.6780 0.02596 0.01729 -0.0200 0.4463 0.9388
3.750 0.7144 0.02615 0.01744 -0.0220 0.4322 0.9487
4.000 0.7551 0.02626 0.01734 -0.0247 0.4197 0.9583
4.250 0.7951 0.02638 0.01753 -0.0277 0.4055 0.9673
4.500 0.8324 0.02657 0.01765 -0.0301 0.3940 0.9776
4.750 0.8787 0.02653 0.01754 -0.0342 0.3815 0.9852
5.000 0.9204 0.02671 0.01775 -0.0377 0.3703 0.9937
5.250 0.9618 0.02670 0.01763 -0.0410 0.3602 1.0000
5.500 0.9738 0.02697 0.01795 -0.0391 0.3524 1.0000
5.750 0.9864 0.02714 0.01813 -0.0371 0.3447 1.0000
6.250 1.0113 0.02767 0.01866 -0.0330 0.3311 1.0000
6.500 1.0237 0.02788 0.01885 -0.0309 0.3244 1.0000
6.750 1.0398 0.02813 0.01895 -0.0293 0.3184 1.0000
7.000 1.0448 0.02852 0.01951 -0.0259 0.3116 1.0000
7.250 1.0557 0.02876 0.01974 -0.0234 0.3052 1.0000
7.500 1.0711 0.02905 0.01989 -0.0216 0.2996 1.0000
7.750 1.0726 0.02951 0.02053 -0.0176 0.2935 1.0000
8.000 1.0803 0.02976 0.02077 -0.0145 0.2870 1.0000
8.250 1.0920 0.03002 0.02091 -0.0120 0.2808 1.0000
8.500 1.0887 0.03046 0.02151 -0.0071 0.2745 1.0000
8.750 1.0939 0.03071 0.02173 -0.0036 0.2683 1.0000
9.000 1.1013 0.03106 0.02200 -0.0004 0.2625 1.0000
9.250 1.0940 0.03154 0.02263 0.0051 0.2565 1.0000
9.500 1.0953 0.03181 0.02286 0.0092 0.2502 1.0000
9.750 1.0924 0.03220 0.02323 0.0140 0.2444 1.0000
10.000 1.0783 0.03270 0.02383 0.0203 0.2384 1.0000
10.250 1.0776 0.03302 0.02405 0.0244 0.2316 1.0000
10.500 1.0666 0.03386 0.02501 0.0294 0.2244 1.0000
10.750 1.0634 0.03454 0.02565 0.0331 0.2162 1.0000
11.000 1.0535 0.03581 0.02701 0.0368 0.2068 1.0000
11.250 1.0482 0.03706 0.02822 0.0396 0.1969 1.0000
11.500 1.0408 0.03868 0.02980 0.0421 0.1862 1.0000
11.750 1.0309 0.04086 0.03202 0.0442 0.1750 1.0000
12.000 1.0244 0.04313 0.03426 0.0458 0.1651 1.0000
12.250 1.0231 0.04519 0.03620 0.0469 0.1574 1.0000
12.500 1.0220 0.04743 0.03846 0.0477 0.1506 1.0000
12.750 1.0261 0.04936 0.04031 0.0485 0.1456 1.0000
13.000 1.0282 0.05157 0.04258 0.0490 0.1411 1.0000
13.250 1.0382 0.05304 0.04394 0.0495 0.1376 1.0000
13.500 1.0440 0.05509 0.04602 0.0499 0.1346 1.0000
13.750 1.0456 0.05757 0.04862 0.0502 0.1319 1.0000
14.000 1.0522 0.05956 0.05064 0.0504 0.1295 1.0000
14.250 1.0670 0.06077 0.05176 0.0507 0.1273 1.0000
14.500 1.0811 0.06221 0.05315 0.0510 0.1255 1.0000
14.750 1.0741 0.06575 0.05691 0.0508 0.1241 1.0000
15.000 1.0666 0.06947 0.06082 0.0503 0.1229 1.0000
15.250 1.0576 0.07352 0.06505 0.0495 0.1218 1.0000
15.500 1.0447 0.07820 0.06991 0.0484 0.1209 1.0000
15.750 1.0184 0.08480 0.07675 0.0463 0.1204 1.0000
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Polar data table (+)
Polar graphs
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