WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Reynolds number: 500,000 Max Cl/Cd: 103.29 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66a175-il-500000.txt Download as CSV file: xf-fx66a175-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17A-175 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.1273 0.11012 0.10653 -0.0687 0.6253 0.0185
-12.500 -0.1262 0.10566 0.10208 -0.0706 0.6211 0.0185
-12.250 -0.1385 0.09836 0.09481 -0.0731 0.6193 0.0192
-12.000 -0.1356 0.09494 0.09135 -0.0742 0.6147 0.0195
-11.750 -0.1306 0.09213 0.08851 -0.0751 0.6104 0.0200
-11.500 -0.1299 0.08795 0.08433 -0.0767 0.6066 0.0202
-11.250 -0.1270 0.08463 0.08100 -0.0779 0.6026 0.0210
-11.000 -0.1310 0.07936 0.07572 -0.0800 0.5999 0.0214
-10.750 -0.1363 0.07387 0.07022 -0.0823 0.5975 0.0222
-10.500 -0.1580 0.06322 0.05961 -0.0874 0.5971 0.0215
-9.000 -0.3741 0.03454 0.02944 -0.1069 0.5943 0.0122
-8.750 -0.3752 0.03080 0.02537 -0.1055 0.5905 0.0116
-8.500 -0.3665 0.02808 0.02228 -0.1042 0.5866 0.0117
-8.250 -0.3530 0.02568 0.01956 -0.1030 0.5829 0.0116
-8.000 -0.3351 0.02387 0.01752 -0.1022 0.5789 0.0119
-7.750 -0.3146 0.02261 0.01605 -0.1015 0.5748 0.0123
-7.500 -0.2926 0.02170 0.01494 -0.1008 0.5710 0.0127
-7.250 -0.2721 0.02022 0.01324 -0.1000 0.5675 0.0134
-7.000 -0.2527 0.01855 0.01149 -0.0991 0.5639 0.0141
-6.750 -0.2307 0.01764 0.01053 -0.0984 0.5603 0.0147
-6.500 -0.2082 0.01692 0.00971 -0.0978 0.5569 0.0153
-6.250 -0.1850 0.01632 0.00901 -0.0972 0.5536 0.0161
-6.000 -0.1616 0.01565 0.00829 -0.0967 0.5501 0.0169
-5.750 -0.1364 0.01525 0.00783 -0.0964 0.5467 0.0181
-5.500 -0.1143 0.01441 0.00686 -0.0958 0.5436 0.0196
-5.250 -0.0904 0.01384 0.00618 -0.0954 0.5406 0.0215
-5.000 -0.0646 0.01343 0.00571 -0.0952 0.5378 0.0238
-4.750 -0.0385 0.01303 0.00523 -0.0950 0.5349 0.0273
-4.500 -0.0135 0.01243 0.00466 -0.0947 0.5320 0.0471
-4.250 0.0074 0.01117 0.00400 -0.0945 0.5295 0.1943
-4.000 0.0287 0.01012 0.00362 -0.0942 0.5270 0.3877
-3.750 0.0568 0.01024 0.00376 -0.0942 0.5244 0.4366
-3.500 0.0855 0.01039 0.00385 -0.0943 0.5218 0.4571
-3.250 0.1139 0.01058 0.00398 -0.0943 0.5192 0.4720
-3.000 0.1422 0.01075 0.00410 -0.0943 0.5167 0.4826
-2.750 0.1704 0.01094 0.00420 -0.0942 0.5143 0.4928
-2.500 0.1988 0.01120 0.00436 -0.0943 0.5120 0.5021
-2.250 0.2269 0.01129 0.00446 -0.0943 0.5098 0.5089
-2.000 0.2552 0.01139 0.00453 -0.0943 0.5075 0.5152
-1.750 0.2837 0.01145 0.00449 -0.0945 0.5052 0.5184
-1.500 0.3120 0.01139 0.00442 -0.0947 0.5029 0.5210
-1.250 0.3403 0.01141 0.00441 -0.0948 0.5007 0.5237
-1.000 0.3688 0.01147 0.00440 -0.0950 0.4986 0.5262
-0.750 0.3974 0.01157 0.00441 -0.0953 0.4963 0.5282
-0.500 0.4256 0.01155 0.00438 -0.0955 0.4943 0.5301
-0.250 0.4540 0.01158 0.00437 -0.0957 0.4921 0.5320
0.000 0.4823 0.01158 0.00434 -0.0959 0.4899 0.5336
0.250 0.5105 0.01156 0.00431 -0.0960 0.4878 0.5351
0.500 0.5387 0.01157 0.00430 -0.0962 0.4857 0.5366
0.750 0.5670 0.01164 0.00432 -0.0965 0.4836 0.5382
1.000 0.5953 0.01173 0.00439 -0.0967 0.4815 0.5399
1.250 0.6232 0.01175 0.00443 -0.0968 0.4796 0.5417
1.500 0.6512 0.01179 0.00448 -0.0970 0.4776 0.5435
1.750 0.6793 0.01184 0.00452 -0.0972 0.4757 0.5452
2.000 0.7074 0.01190 0.00457 -0.0974 0.4738 0.5470
2.250 0.7354 0.01193 0.00459 -0.0976 0.4720 0.5489
2.500 0.7634 0.01199 0.00466 -0.0978 0.4703 0.5509
2.750 0.7918 0.01215 0.00480 -0.0981 0.4684 0.5528
3.000 0.8194 0.01223 0.00492 -0.0983 0.4670 0.5547
3.250 0.8469 0.01229 0.00505 -0.0984 0.4654 0.5568
3.500 0.8745 0.01238 0.00517 -0.0985 0.4637 0.5590
3.750 0.9022 0.01248 0.00529 -0.0987 0.4621 0.5611
4.000 0.9298 0.01256 0.00541 -0.0988 0.4605 0.5634
4.250 0.9574 0.01264 0.00554 -0.0990 0.4590 0.5660
4.500 0.9851 0.01275 0.00568 -0.0992 0.4576 0.5688
4.750 1.0130 0.01288 0.00584 -0.0994 0.4562 0.5720
5.000 1.0412 0.01310 0.00607 -0.0998 0.4547 0.5749
5.250 1.0686 0.01329 0.00631 -0.1000 0.4534 0.5776
5.500 1.0950 0.01338 0.00652 -0.0999 0.4521 0.5806
5.750 1.1215 0.01351 0.00675 -0.0999 0.4507 0.5842
6.000 1.1482 0.01366 0.00699 -0.1000 0.4492 0.5882
6.250 1.1750 0.01380 0.00722 -0.1001 0.4477 0.5922
6.500 1.2016 0.01392 0.00743 -0.1001 0.4461 0.5964
6.750 1.2286 0.01404 0.00763 -0.1002 0.4444 0.6014
7.000 1.2561 0.01408 0.00764 -0.1003 0.4402 0.6068
7.250 1.2759 0.01375 0.00749 -0.0989 0.4328 0.6125
7.500 1.3001 0.01363 0.00732 -0.0983 0.4253 0.6199
7.750 1.3208 0.01344 0.00736 -0.0971 0.4188 0.6282
8.000 1.3424 0.01333 0.00730 -0.0961 0.4104 0.6389
8.250 1.3613 0.01318 0.00727 -0.0945 0.3955 0.6532
8.500 1.3577 0.01389 0.00764 -0.0892 0.3157 0.6713
8.750 1.3309 0.01578 0.00916 -0.0806 0.2367 0.6978
9.000 1.2956 0.01773 0.01115 -0.0712 0.1770 0.8165
9.250 1.2693 0.02071 0.01404 -0.0661 0.1195 1.0000
9.500 1.2475 0.02383 0.01707 -0.0625 0.0891 1.0000
9.750 1.2158 0.02877 0.02189 -0.0602 0.0528 1.0000
10.000 1.1913 0.03360 0.02665 -0.0589 0.0255 1.0000
10.250 1.1744 0.03777 0.03083 -0.0579 0.0139 1.0000
10.500 1.1687 0.04091 0.03404 -0.0571 0.0115 1.0000
10.750 1.1658 0.04377 0.03699 -0.0565 0.0098 1.0000
11.000 1.1634 0.04661 0.03989 -0.0560 0.0091 1.0000
11.250 1.1592 0.04968 0.04304 -0.0555 0.0085 1.0000
11.500 1.1523 0.05313 0.04659 -0.0551 0.0079 1.0000
11.750 1.1494 0.05629 0.04983 -0.0548 0.0077 1.0000
12.000 1.1518 0.05892 0.05253 -0.0547 0.0075 1.0000
12.250 1.1501 0.06209 0.05578 -0.0546 0.0074 1.0000
12.500 1.1499 0.06513 0.05889 -0.0546 0.0072 1.0000
12.750 1.1492 0.06831 0.06214 -0.0547 0.0068 1.0000
13.000 1.1491 0.07142 0.06532 -0.0548 0.0067 1.0000
13.250 1.1486 0.07465 0.06861 -0.0549 0.0064 1.0000
13.500 1.1480 0.07793 0.07195 -0.0552 0.0060 1.0000
13.750 1.1473 0.08127 0.07536 -0.0554 0.0060 1.0000
14.000 1.1477 0.08445 0.07861 -0.0557 0.0058 1.0000
14.250 1.1454 0.08804 0.08225 -0.0561 0.0056 1.0000
14.500 1.1505 0.09068 0.08496 -0.0564 0.0059 1.0000
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