FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: FX 61-163 AIRFOIL (fx61163-il) Reynolds number: 50,000 Max Cl/Cd: 6.11 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61163-il-50000.txt Download as CSV file: xf-fx61163-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-163 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3509 0.12833 0.12171 -0.0263 1.0001 0.3019
-10.500 -0.3204 0.12248 0.11583 -0.0260 1.0001 0.3094
-10.250 -0.3231 0.11982 0.11326 -0.0262 1.0001 0.3195
-9.750 -0.3150 0.11325 0.10683 -0.0264 1.0001 0.3347
-9.500 -0.3097 0.10954 0.10318 -0.0269 1.0001 0.3366
-9.250 -0.3946 0.09215 0.08611 -0.0469 1.0001 0.1768
-9.000 -0.4561 0.08214 0.07635 -0.0547 1.0001 0.1565
-8.750 -0.4855 0.07718 0.07152 -0.0552 1.0001 0.1450
-8.500 -0.5364 0.07475 0.06928 -0.0530 1.0001 0.1427
-8.250 -0.5802 0.07412 0.06878 -0.0483 1.0001 0.1419
-8.000 -0.6273 0.07350 0.06813 -0.0443 1.0001 0.1406
-7.750 -0.6334 0.07089 0.06550 -0.0420 1.0001 0.1334
-7.500 -0.6683 0.06759 0.06164 -0.0414 1.0001 0.1235
-7.250 -0.6652 0.06416 0.05822 -0.0401 1.0001 0.1196
-7.000 -0.6725 0.06036 0.05350 -0.0406 1.0001 0.1096
-6.750 -0.6624 0.05689 0.04994 -0.0401 1.0001 0.1075
-6.500 -0.6508 0.05362 0.04637 -0.0400 1.0001 0.1050
-6.250 -0.6354 0.05040 0.04269 -0.0403 1.0001 0.1019
-6.000 -0.5932 0.04702 0.03819 -0.0444 0.9946 0.0964
-5.750 -0.5555 0.04437 0.03510 -0.0467 0.9886 0.0952
-5.500 -0.5170 0.04203 0.03237 -0.0487 0.9829 0.0953
-5.250 -0.4835 0.03992 0.03015 -0.0494 0.9769 0.0976
-5.000 -0.4497 0.03865 0.02893 -0.0498 0.9714 0.1048
-4.750 -0.4225 0.03785 0.02805 -0.0483 0.9654 0.1117
-4.500 -0.3901 0.03717 0.02739 -0.0477 0.9601 0.1240
-4.250 -0.3705 0.03603 0.02652 -0.0469 0.9541 0.1434
-4.000 -0.3406 0.03150 0.02484 -0.0508 0.9495 0.4069
-3.750 -0.3621 0.03862 0.03237 -0.0293 0.9429 0.6646
-3.500 -0.2288 0.04891 0.04175 -0.0122 0.9409 0.8629
-3.250 -0.1616 0.04774 0.04006 -0.0207 0.9349 0.8832
-3.000 -0.1223 0.04697 0.03897 -0.0250 0.9286 0.8980
-2.750 -0.1016 0.04648 0.03828 -0.0262 0.9218 0.9088
-2.500 -0.0634 0.04593 0.03745 -0.0305 0.9158 0.9197
-2.250 -0.0361 0.04548 0.03682 -0.0329 0.9087 0.9288
-2.000 0.0110 0.04496 0.03605 -0.0387 0.9028 0.9386
-1.750 0.0162 0.04501 0.03600 -0.0372 0.8958 0.9453
-1.500 0.0581 0.04469 0.03549 -0.0422 0.8895 0.9530
-1.250 0.0704 0.04483 0.03554 -0.0420 0.8830 0.9591
-1.000 0.1016 0.04479 0.03537 -0.0451 0.8761 0.9653
-0.750 0.1287 0.04494 0.03539 -0.0474 0.8699 0.9713
-0.500 0.1491 0.04518 0.03555 -0.0487 0.8627 0.9767
-0.250 0.1902 0.04533 0.03558 -0.0534 0.8561 0.9825
0.000 0.1985 0.04589 0.03610 -0.0528 0.8489 0.9871
0.250 0.2505 0.04605 0.03616 -0.0591 0.8419 0.9924
0.500 0.2478 0.04694 0.03705 -0.0569 0.8352 0.9965
0.750 0.2894 0.04733 0.03736 -0.0613 0.8281 0.9999
1.000 0.2672 0.04840 0.03845 -0.0557 0.8226 0.9999
1.250 0.2641 0.04920 0.03924 -0.0529 0.8168 0.9999
1.500 0.2760 0.04994 0.03994 -0.0523 0.8108 0.9999
1.750 0.2543 0.05089 0.04091 -0.0469 0.8067 0.9999
2.000 0.2511 0.05168 0.04169 -0.0442 0.8016 0.9999
2.250 0.2618 0.05250 0.04249 -0.0434 0.7958 0.9999
2.500 0.2417 0.05336 0.04336 -0.0386 0.7937 0.9999
2.750 0.2273 0.05417 0.04419 -0.0347 0.7923 0.9999
3.000 0.2158 0.05504 0.04506 -0.0313 0.7933 0.9999
3.250 0.2116 0.05608 0.04610 -0.0291 0.7960 0.9999
3.500 0.0305 0.05405 0.04435 -0.0060 0.9489 0.9999
3.750 0.0610 0.05589 0.04616 -0.0097 0.9346 0.9999
4.000 0.0907 0.05774 0.04799 -0.0133 0.9201 0.9999
4.250 0.1200 0.05962 0.04986 -0.0167 0.9056 0.9999
4.500 0.1499 0.06161 0.05185 -0.0202 0.8906 0.9999
4.750 0.1791 0.06363 0.05387 -0.0235 0.8757 0.9999
5.000 0.2075 0.06568 0.05594 -0.0266 0.8608 0.9999
5.250 0.2353 0.06776 0.05805 -0.0296 0.8458 0.9999
5.500 0.2617 0.06984 0.06016 -0.0324 0.8311 0.9999
5.750 0.2874 0.07197 0.06233 -0.0350 0.8165 0.9999
6.000 0.3117 0.07412 0.06455 -0.0375 0.8022 0.9999
6.250 0.3361 0.07636 0.06684 -0.0399 0.7878 0.9999
6.500 0.3599 0.07866 0.06921 -0.0423 0.7735 0.9999
6.750 0.3833 0.08104 0.07165 -0.0446 0.7593 0.9999
7.000 0.4068 0.08344 0.07414 -0.0469 0.7441 0.9999
7.250 0.4293 0.08591 0.07670 -0.0490 0.7297 0.9999
7.500 0.4513 0.08842 0.07929 -0.0511 0.7147 0.9999
7.750 0.4728 0.09104 0.08200 -0.0532 0.7006 0.9999
8.000 0.4939 0.09373 0.08482 -0.0552 0.6863 0.9999
8.250 0.5161 0.09662 0.08782 -0.0573 0.6728 0.9999
8.500 0.5375 0.09951 0.09081 -0.0593 0.6585 0.9999
8.750 0.5580 0.10241 0.09383 -0.0612 0.6439 0.9999
9.000 0.5776 0.10535 0.09690 -0.0630 0.6291 0.9999
9.250 0.5969 0.10834 0.10001 -0.0647 0.6144 0.9999
9.500 0.6161 0.11140 0.10320 -0.0664 0.5996 0.9999
9.750 0.6359 0.11458 0.10651 -0.0681 0.5849 0.9999
10.000 0.6543 0.11773 0.10981 -0.0697 0.5702 0.9999
10.250 0.6700 0.12077 0.11297 -0.0710 0.5554 0.9999
10.500 0.6584 0.12288 0.11516 -0.0711 0.5454 0.9999
10.750 0.6685 0.12609 0.11847 -0.0724 0.5330 0.9999
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