GRUMMAN K-3 AIRFOIL (k3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GRUMMAN K-3 AIRFOIL (k3-il) Reynolds number: 200,000 Max Cl/Cd: 49.16 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k3-il-200000.txt Download as CSV file: xf-k3-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GRUMMAN K-3 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
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9289 0.09436 0.08885 -0.0770 0.9999 0.0768
-17.750 -1.0037 0.08112 0.07520 -0.0829 0.9999 0.0768
-17.500 -1.0396 0.07441 0.06825 -0.0848 0.9999 0.0772
-17.250 -1.0674 0.06920 0.06281 -0.0857 0.9999 0.0777
-17.000 -1.0922 0.06482 0.05821 -0.0860 0.9999 0.0782
-16.750 -1.1151 0.06096 0.05412 -0.0857 0.9999 0.0787
-16.500 -1.1182 0.05873 0.05182 -0.0847 0.9999 0.0795
-16.250 -1.1054 0.05794 0.05111 -0.0836 0.9999 0.0805
-16.000 -1.1042 0.05638 0.04954 -0.0825 0.9999 0.0815
-15.750 -1.1083 0.05445 0.04754 -0.0813 0.9999 0.0824
-15.500 -1.1155 0.05238 0.04536 -0.0799 0.9999 0.0834
-15.250 -1.1245 0.05028 0.04313 -0.0783 0.9999 0.0845
-15.000 -1.1360 0.04820 0.04087 -0.0765 0.9999 0.0854
-14.750 -1.1451 0.04633 0.03886 -0.0744 0.9999 0.0864
-14.500 -1.1296 0.04573 0.03840 -0.0729 0.9999 0.0879
-14.250 -1.1271 0.04471 0.03739 -0.0709 0.9999 0.0892
-14.000 -1.1304 0.04344 0.03608 -0.0687 0.9999 0.0905
-13.750 -1.1379 0.04206 0.03459 -0.0660 0.9999 0.0918
-13.500 -1.1499 0.04066 0.03306 -0.0628 0.9999 0.0930
-13.250 -1.1672 0.03939 0.03164 -0.0586 0.9999 0.0939
-13.000 -1.1528 0.03872 0.03111 -0.0568 0.9999 0.0957
-12.750 -1.1563 0.03785 0.03027 -0.0536 0.9999 0.0971
-12.500 -1.1549 0.03679 0.02917 -0.0516 0.9999 0.0987
-12.250 -1.1514 0.03558 0.02784 -0.0502 0.9999 0.1007
-12.000 -1.1439 0.03437 0.02651 -0.0492 0.9999 0.1027
-11.750 -1.1308 0.03358 0.02582 -0.0479 0.9999 0.1048
-11.500 -1.1181 0.03273 0.02496 -0.0472 0.9999 0.1073
-11.250 -1.1044 0.03181 0.02390 -0.0467 0.9999 0.1103
-11.000 -1.0888 0.03096 0.02309 -0.0459 0.9999 0.1130
-10.750 -1.0717 0.03026 0.02243 -0.0455 0.9999 0.1161
-10.500 -1.0531 0.02953 0.02156 -0.0455 0.9999 0.1199
-10.250 -1.0250 0.02880 0.02092 -0.0469 0.9982 0.1239
-10.000 -0.9936 0.02824 0.02031 -0.0491 0.9960 0.1290
-9.750 -0.9623 0.02762 0.01973 -0.0512 0.9941 0.1341
-9.500 -0.9287 0.02717 0.01923 -0.0536 0.9921 0.1403
-9.250 -0.9008 0.02652 0.01866 -0.0549 0.9896 0.1459
-9.000 -0.8700 0.02610 0.01813 -0.0567 0.9873 0.1528
-8.750 -0.8394 0.02557 0.01773 -0.0585 0.9853 0.1596
-8.500 -0.8052 0.02516 0.01733 -0.0608 0.9834 0.1675
-8.250 -0.7680 0.02491 0.01706 -0.0637 0.9817 0.1762
-8.000 -0.7367 0.02444 0.01669 -0.0655 0.9789 0.1844
-7.750 -0.7078 0.02406 0.01631 -0.0667 0.9765 0.1932
-7.500 -0.6765 0.02371 0.01602 -0.0684 0.9744 0.2030
-7.250 -0.6432 0.02335 0.01574 -0.0705 0.9727 0.2137
-7.000 -0.6083 0.02307 0.01551 -0.0728 0.9712 0.2262
-6.750 -0.5705 0.02283 0.01533 -0.0757 0.9698 0.2410
-6.500 -0.5301 0.02259 0.01521 -0.0792 0.9685 0.2589
-6.250 -0.4992 0.02220 0.01495 -0.0808 0.9656 0.2781
-6.000 -0.4667 0.02183 0.01478 -0.0828 0.9637 0.3033
-5.750 -0.4314 0.02154 0.01472 -0.0853 0.9620 0.3377
-5.500 -0.3955 0.02141 0.01483 -0.0878 0.9604 0.3800
-5.250 -0.3596 0.02152 0.01513 -0.0899 0.9585 0.4190
-5.000 -0.3224 0.02181 0.01546 -0.0920 0.9566 0.4497
-4.750 -0.2861 0.02225 0.01595 -0.0938 0.9551 0.4716
-4.500 -0.2566 0.02267 0.01635 -0.0944 0.9530 0.4889
-4.250 -0.2392 0.02298 0.01676 -0.0924 0.9487 0.4988
-4.000 -0.2084 0.02332 0.01705 -0.0932 0.9458 0.5118
-3.750 -0.1801 0.02382 0.01764 -0.0931 0.9436 0.5206
-3.500 -0.1430 0.02424 0.01798 -0.0951 0.9417 0.5326
-3.250 -0.1087 0.02481 0.01866 -0.0959 0.9400 0.5397
-3.000 -0.0959 0.02510 0.01899 -0.0933 0.9346 0.5467
-2.750 -0.0646 0.02537 0.01920 -0.0943 0.9311 0.5555
-2.500 -0.0355 0.02579 0.01972 -0.0942 0.9283 0.5610
-2.250 0.0001 0.02621 0.02019 -0.0954 0.9262 0.5681
-2.000 0.0443 0.02654 0.02044 -0.0988 0.9247 0.5773
-1.750 0.0513 0.02671 0.02072 -0.0949 0.9165 0.5811
-1.500 0.0827 0.02703 0.02112 -0.0951 0.9129 0.5865
-1.250 0.1226 0.02726 0.02138 -0.0972 0.9105 0.5936
-1.000 0.1521 0.02744 0.02151 -0.0980 0.9047 0.6008
-0.750 0.1769 0.02755 0.02174 -0.0970 0.8987 0.6052
-0.500 0.2131 0.02768 0.02197 -0.0978 0.8952 0.6112
-0.250 0.2475 0.02759 0.02192 -0.0985 0.8879 0.6181
0.000 0.3296 0.02527 0.01957 -0.1061 0.8766 0.6258
0.250 0.3626 0.02434 0.01872 -0.1056 0.8637 0.6292
0.500 0.4091 0.02347 0.01793 -0.1078 0.8601 0.6331
0.750 0.4605 0.02246 0.01699 -0.1111 0.8579 0.6377
1.000 0.4797 0.02244 0.01701 -0.1094 0.8463 0.6421
1.250 0.5361 0.02115 0.01572 -0.1139 0.8428 0.6475
1.500 0.5934 0.01955 0.01423 -0.1179 0.8402 0.6509
1.750 0.6123 0.01923 0.01400 -0.1154 0.8273 0.6537
2.000 0.6769 0.01762 0.01247 -0.1207 0.8201 0.6574
2.250 0.7042 0.01708 0.01198 -0.1196 0.8020 0.6615
2.500 0.7367 0.01650 0.01142 -0.1196 0.7767 0.6659
2.750 0.7782 0.01583 0.01061 -0.1212 0.7238 0.6701
3.000 0.7994 0.01637 0.00998 -0.1186 0.5181 0.6729
3.250 0.7889 0.01775 0.01063 -0.1111 0.3926 0.6755
3.500 0.7843 0.01892 0.01129 -0.1050 0.3056 0.6785
3.750 0.7925 0.01987 0.01190 -0.1015 0.2531 0.6820
4.000 0.8085 0.02065 0.01246 -0.0996 0.2242 0.6858
4.250 0.8293 0.02133 0.01298 -0.0985 0.2052 0.6897
4.500 0.8522 0.02202 0.01351 -0.0980 0.1904 0.6934
4.750 0.8741 0.02242 0.01392 -0.0969 0.1786 0.6965
5.000 0.8945 0.02298 0.01445 -0.0955 0.1685 0.6999
5.250 0.9156 0.02355 0.01497 -0.0944 0.1594 0.7038
5.500 0.9390 0.02404 0.01548 -0.0937 0.1508 0.7080
5.750 0.9620 0.02473 0.01603 -0.0931 0.1429 0.7121
6.000 0.9868 0.02516 0.01650 -0.0928 0.1349 0.7161
6.250 1.0073 0.02572 0.01705 -0.0915 0.1278 0.7194
6.500 1.0274 0.02621 0.01756 -0.0902 0.1207 0.7232
6.750 1.0483 0.02678 0.01817 -0.0891 0.1134 0.7278
7.000 1.0691 0.02744 0.01879 -0.0881 0.1064 0.7326
7.250 1.0906 0.02806 0.01937 -0.0874 0.0991 0.7372
7.500 1.1093 0.02860 0.01999 -0.0859 0.0916 0.7409
7.750 1.1271 0.02925 0.02069 -0.0844 0.0843 0.7449
8.000 1.1452 0.02999 0.02144 -0.0829 0.0775 0.7496
8.250 1.1635 0.03082 0.02226 -0.0816 0.0714 0.7549
8.500 1.1813 0.03170 0.02311 -0.0804 0.0664 0.7600
8.750 1.1972 0.03249 0.02395 -0.0786 0.0619 0.7648
9.000 1.2136 0.03346 0.02498 -0.0769 0.0580 0.7701
9.250 1.2295 0.03455 0.02599 -0.0755 0.0552 0.7757
9.500 1.2470 0.03559 0.02716 -0.0742 0.0523 0.7811
9.750 1.2615 0.03667 0.02821 -0.0724 0.0503 0.7862
10.000 1.2775 0.03788 0.02955 -0.0708 0.0484 0.7924
10.250 1.2940 0.03908 0.03080 -0.0696 0.0466 0.7994
10.500 1.3091 0.04023 0.03191 -0.0680 0.0453 0.8057
10.750 1.3236 0.04159 0.03344 -0.0663 0.0439 0.8132
11.000 1.3375 0.04294 0.03493 -0.0647 0.0426 0.8209
11.250 1.3497 0.04417 0.03623 -0.0629 0.0415 0.8285
11.500 1.3678 0.04551 0.03748 -0.0620 0.0405 0.8377
11.750 1.3746 0.04712 0.03935 -0.0595 0.0396 0.8462
12.000 1.3833 0.04885 0.04129 -0.0576 0.0388 0.8570
12.250 1.3893 0.05045 0.04307 -0.0552 0.0381 0.8688
12.500 1.3948 0.05208 0.04486 -0.0528 0.0376 0.8835
12.750 1.3984 0.05363 0.04653 -0.0501 0.0371 0.9035
13.000 1.3962 0.05479 0.04781 -0.0462 0.0368 0.9477
13.250 1.4080 0.05654 0.04955 -0.0453 0.0363 1.0001
13.500 1.4150 0.05936 0.05252 -0.0447 0.0359 1.0001
13.750 1.4098 0.06271 0.05615 -0.0433 0.0357 1.0001
14.000 1.4019 0.06636 0.06007 -0.0421 0.0355 1.0001
14.250 1.3911 0.07035 0.06434 -0.0412 0.0353 1.0001
14.500 1.3776 0.07478 0.06903 -0.0406 0.0352 1.0001
14.750 1.3616 0.07973 0.07425 -0.0407 0.0351 1.0001
15.000 1.3422 0.08538 0.08018 -0.0415 0.0351 1.0001
15.250 1.3191 0.09197 0.08705 -0.0434 0.0351 1.0001
15.500 1.2925 0.09969 0.09506 -0.0468 0.0351 1.0001
15.750 1.2609 0.10905 0.10473 -0.0521 0.0353 1.0001
16.000 1.2242 0.12047 0.11646 -0.0598 0.0355 1.0001
16.250 1.1846 0.13388 0.13015 -0.0698 0.0358 1.0001
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