FX 83-W-160 (fx83w160-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 83-W-160 (fx83w160-il) Reynolds number: 100,000 Max Cl/Cd: 45.31 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx83w160-il-100000.txt Download as CSV file: xf-fx83w160-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 83-W-160
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5458 0.10496 0.10013 -0.0466 1.0000 0.1089
-10.250 -0.5505 0.10181 0.09701 -0.0452 1.0000 0.1078
-10.000 -0.8620 0.06469 0.05914 -0.0596 1.0000 0.0854
-9.750 -0.8784 0.06042 0.05456 -0.0585 1.0000 0.0853
-9.500 -0.8799 0.05696 0.05097 -0.0574 1.0000 0.0862
-9.250 -0.8616 0.05682 0.05106 -0.0558 1.0000 0.0887
-9.000 -0.8620 0.05383 0.04784 -0.0550 1.0000 0.0901
-8.750 -0.8604 0.05051 0.04416 -0.0545 1.0000 0.0919
-8.500 -0.8551 0.04708 0.04026 -0.0542 1.0000 0.0938
-8.250 -0.8409 0.04381 0.03635 -0.0549 0.9989 0.0959
-8.000 -0.8109 0.04164 0.03404 -0.0575 0.9948 0.0998
-7.750 -0.7840 0.04050 0.03278 -0.0587 0.9910 0.1045
-7.500 -0.7559 0.03881 0.03046 -0.0604 0.9874 0.1094
-7.250 -0.7270 0.03747 0.02924 -0.0619 0.9827 0.1148
-7.000 -0.6974 0.03652 0.02800 -0.0633 0.9784 0.1215
-6.750 -0.6675 0.03544 0.02690 -0.0647 0.9744 0.1284
-6.500 -0.6444 0.03474 0.02600 -0.0648 0.9711 0.1360
-6.250 -0.6157 0.03391 0.02520 -0.0658 0.9673 0.1443
-6.000 -0.5844 0.03334 0.02441 -0.0672 0.9628 0.1550
-5.750 -0.5622 0.03269 0.02388 -0.0670 0.9590 0.1648
-5.500 -0.5356 0.03210 0.02329 -0.0675 0.9558 0.1762
-5.250 -0.5004 0.03183 0.02303 -0.0695 0.9522 0.1915
-5.000 -0.4806 0.03130 0.02249 -0.0687 0.9475 0.2052
-4.750 -0.4561 0.03090 0.02218 -0.0689 0.9437 0.2228
-4.500 -0.4290 0.03062 0.02207 -0.0695 0.9408 0.2441
-4.250 -0.3947 0.03055 0.02219 -0.0714 0.9379 0.2769
-4.000 -0.3792 0.03015 0.02199 -0.0700 0.9342 0.3092
-3.750 -0.3581 0.02987 0.02205 -0.0695 0.9302 0.3572
-3.500 -0.3312 0.03010 0.02264 -0.0696 0.9262 0.4182
-3.250 -0.2983 0.03105 0.02373 -0.0704 0.9229 0.4710
-3.000 -0.2844 0.03158 0.02425 -0.0682 0.9195 0.5007
-2.750 -0.2682 0.03222 0.02491 -0.0662 0.9158 0.5238
-2.500 -0.2435 0.03298 0.02563 -0.0656 0.9113 0.5475
-2.250 -0.2088 0.03398 0.02656 -0.0667 0.9074 0.5713
-2.000 -0.1965 0.03438 0.02700 -0.0641 0.9019 0.5861
-1.750 -0.1779 0.03489 0.02752 -0.0625 0.8973 0.6009
-1.500 -0.1480 0.03556 0.02817 -0.0627 0.8927 0.6174
-1.250 -0.1237 0.03613 0.02872 -0.0622 0.8874 0.6323
-1.000 -0.1107 0.03648 0.02903 -0.0603 0.8836 0.6460
-0.750 -0.0885 0.03696 0.02948 -0.0596 0.8789 0.6607
-0.500 -0.0531 0.03764 0.03018 -0.0604 0.8743 0.6758
-0.250 -0.0443 0.03792 0.03048 -0.0576 0.8686 0.6874
0.000 -0.0272 0.03831 0.03085 -0.0563 0.8637 0.7013
0.250 0.0066 0.03882 0.03133 -0.0574 0.8585 0.7165
0.500 0.0215 0.03910 0.03164 -0.0553 0.8513 0.7271
0.750 0.0439 0.03938 0.03191 -0.0549 0.8448 0.7381
1.000 0.0890 0.03988 0.03236 -0.0578 0.8397 0.7503
1.250 0.0914 0.04004 0.03255 -0.0544 0.8311 0.7580
1.500 0.1226 0.04045 0.03292 -0.0555 0.8257 0.7693
1.750 0.1500 0.04082 0.03332 -0.0556 0.8194 0.7783
2.000 0.1672 0.04113 0.03361 -0.0548 0.8110 0.7877
2.250 0.2093 0.04135 0.03386 -0.0569 0.8058 0.7971
2.500 0.2179 0.04168 0.03419 -0.0548 0.7950 0.8062
2.750 0.2576 0.04181 0.03435 -0.0564 0.7894 0.8167
3.000 0.2686 0.04225 0.03483 -0.0547 0.7794 0.8267
3.250 0.3060 0.04241 0.03500 -0.0563 0.7732 0.8387
3.500 0.3227 0.04283 0.03548 -0.0552 0.7637 0.8493
3.750 0.3598 0.04284 0.03553 -0.0567 0.7565 0.8615
4.000 0.3813 0.04311 0.03586 -0.0562 0.7458 0.8749
4.250 0.4219 0.04288 0.03571 -0.0579 0.7391 0.8919
4.500 0.4450 0.04318 0.03614 -0.0580 0.7281 0.9137
4.750 0.5071 0.04265 0.03577 -0.0636 0.7216 0.9613
5.000 0.5341 0.04287 0.03600 -0.0646 0.7088 1.0000
5.250 0.5978 0.04169 0.03483 -0.0692 0.7035 1.0000
5.500 0.6264 0.04168 0.03484 -0.0699 0.6899 1.0000
5.750 0.6937 0.03974 0.03294 -0.0742 0.6860 1.0000
6.000 0.7176 0.03975 0.03295 -0.0739 0.6722 1.0000
6.250 0.7834 0.03732 0.03059 -0.0774 0.6692 1.0000
6.500 0.8054 0.03717 0.03047 -0.0764 0.6552 1.0000
6.750 0.8670 0.03447 0.02787 -0.0789 0.6526 1.0000
7.000 0.8906 0.03394 0.02739 -0.0776 0.6390 1.0000
7.250 0.9578 0.03045 0.02401 -0.0803 0.6358 1.0000
7.500 0.9877 0.02924 0.02287 -0.0792 0.6209 1.0000
7.750 1.0239 0.02767 0.02137 -0.0787 0.6048 1.0000
8.000 1.0663 0.02583 0.01957 -0.0790 0.5841 1.0000
8.250 1.0834 0.02548 0.01921 -0.0764 0.5528 1.0000
8.500 1.1055 0.02500 0.01859 -0.0744 0.5086 1.0000
8.750 1.1268 0.02487 0.01801 -0.0723 0.4456 1.0000
9.000 1.1316 0.02595 0.01859 -0.0688 0.3874 1.0000
9.250 1.1350 0.02737 0.01953 -0.0655 0.3426 1.0000
9.500 1.1403 0.02881 0.02064 -0.0627 0.3082 1.0000
9.750 1.1485 0.03019 0.02181 -0.0604 0.2809 1.0000
10.000 1.1614 0.03149 0.02283 -0.0588 0.2589 1.0000
10.250 1.1749 0.03275 0.02394 -0.0573 0.2399 1.0000
10.500 1.1918 0.03396 0.02500 -0.0562 0.2237 1.0000
10.750 1.2091 0.03517 0.02610 -0.0552 0.2091 1.0000
11.000 1.2237 0.03642 0.02738 -0.0539 0.1964 1.0000
11.250 1.2417 0.03770 0.02864 -0.0530 0.1846 1.0000
11.500 1.2636 0.03896 0.02977 -0.0526 0.1736 1.0000
11.750 1.2775 0.04025 0.03112 -0.0513 0.1641 1.0000
12.000 1.2953 0.04170 0.03260 -0.0505 0.1549 1.0000
12.250 1.3189 0.04297 0.03371 -0.0503 0.1460 1.0000
12.500 1.3276 0.04461 0.03557 -0.0486 0.1392 1.0000
12.750 1.3503 0.04592 0.03676 -0.0484 0.1317 1.0000
13.000 1.3602 0.04776 0.03882 -0.0468 0.1259 1.0000
13.250 1.3717 0.04933 0.04047 -0.0455 0.1204 1.0000
13.500 1.3947 0.05115 0.04226 -0.0455 0.1146 1.0000
13.750 1.3959 0.05320 0.04460 -0.0433 0.1106 1.0000
14.000 1.4068 0.05496 0.04643 -0.0421 0.1064 1.0000
14.250 1.4269 0.05716 0.04864 -0.0419 0.1019 1.0000
14.500 1.4192 0.05978 0.05160 -0.0393 0.0994 1.0000
14.750 1.4182 0.06224 0.05428 -0.0375 0.0964 1.0000
15.000 1.4257 0.06430 0.05640 -0.0365 0.0934 1.0000
15.250 1.4401 0.06707 0.05920 -0.0361 0.0904 1.0000
15.500 1.4194 0.07072 0.06323 -0.0336 0.0892 1.0000
15.750 1.3993 0.07476 0.06763 -0.0318 0.0881 1.0000
16.000 1.3782 0.07916 0.07234 -0.0304 0.0870 1.0000
16.250 1.3559 0.08393 0.07740 -0.0296 0.0860 1.0000
16.500 1.3300 0.08942 0.08319 -0.0295 0.0853 1.0000
16.750 1.2961 0.09623 0.09030 -0.0304 0.0852 1.0000
17.000 1.2468 0.10575 0.10017 -0.0332 0.0860 1.0000
17.250 1.1803 0.11952 0.11428 -0.0396 0.0880 1.0000
17.500 1.1112 0.13690 0.13185 -0.0495 0.0901 1.0000
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