S3014-095-85 (s3014-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3014-095-85 (s3014-il) Reynolds number: 200,000 Max Cl/Cd: 70.27 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3014-il-200000.txt Download as CSV file: xf-s3014-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S3014-095-85
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4398 0.09635 0.09299 -0.0224 1.0000 0.0463
-9.000 -0.4296 0.09358 0.09023 -0.0219 1.0000 0.0476
-8.750 -0.4239 0.09048 0.08715 -0.0228 1.0000 0.0491
-8.500 -0.4208 0.08715 0.08385 -0.0244 1.0000 0.0513
-8.250 -0.4206 0.08350 0.08024 -0.0268 1.0000 0.0530
-8.000 -0.3675 0.06692 0.06399 -0.0349 1.0000 0.0588
-7.750 -0.3577 0.06420 0.06130 -0.0337 1.0000 0.0606
-7.500 -0.3612 0.06067 0.05782 -0.0350 1.0000 0.0618
-7.250 -0.3841 0.05831 0.05556 -0.0339 1.0000 0.0618
-7.000 -0.4117 0.05666 0.05397 -0.0311 1.0000 0.0616
-6.500 -0.4721 0.05917 0.05610 -0.0343 0.9995 0.0617
-6.250 -0.4453 0.05147 0.04754 -0.0457 0.9898 0.0707
-6.000 -0.4189 0.04697 0.04326 -0.0477 0.9863 0.0728
-5.750 -0.3879 0.04387 0.04008 -0.0507 0.9822 0.0767
-5.500 -0.3619 0.03937 0.03512 -0.0541 0.9749 0.0864
-5.250 -0.3271 0.02824 0.02248 -0.0550 0.9705 0.0434
-5.000 -0.3000 0.02500 0.01881 -0.0554 0.9638 0.0422
-4.750 -0.2639 0.02241 0.01579 -0.0571 0.9600 0.0419
-4.500 -0.2251 0.02000 0.01297 -0.0590 0.9572 0.0406
-4.250 -0.1949 0.01847 0.01119 -0.0591 0.9505 0.0405
-4.000 -0.1593 0.01717 0.00974 -0.0603 0.9459 0.0413
-3.750 -0.1248 0.01615 0.00863 -0.0614 0.9412 0.0430
-3.500 -0.0976 0.01533 0.00776 -0.0611 0.9335 0.0460
-3.250 -0.0662 0.01448 0.00690 -0.0616 0.9285 0.0503
-3.000 -0.0423 0.01401 0.00638 -0.0605 0.9193 0.0555
-2.750 -0.0160 0.01322 0.00569 -0.0598 0.9127 0.0833
-2.500 0.0034 0.01205 0.00540 -0.0585 0.9037 0.2773
-2.250 0.0235 0.01136 0.00531 -0.0571 0.8955 0.4354
-2.000 0.0423 0.01069 0.00526 -0.0548 0.8878 0.5999
-1.750 0.0604 0.01018 0.00529 -0.0519 0.8790 0.7560
-1.500 0.1391 0.00979 0.00519 -0.0603 0.8778 0.9574
-1.250 0.1975 0.00969 0.00491 -0.0660 0.8732 0.9899
-1.000 0.2361 0.00961 0.00468 -0.0682 0.8641 1.0000
-0.750 0.2558 0.00959 0.00453 -0.0664 0.8540 1.0000
-0.500 0.2761 0.00956 0.00437 -0.0646 0.8438 1.0000
-0.250 0.2974 0.00956 0.00428 -0.0631 0.8322 1.0000
0.000 0.3193 0.00955 0.00417 -0.0616 0.8210 1.0000
0.250 0.3416 0.00954 0.00405 -0.0602 0.8104 1.0000
0.500 0.3644 0.00951 0.00392 -0.0588 0.8000 1.0000
0.750 0.3877 0.00951 0.00385 -0.0576 0.7877 1.0000
1.000 0.4114 0.00952 0.00379 -0.0565 0.7756 1.0000
1.250 0.4354 0.00952 0.00373 -0.0555 0.7635 1.0000
1.500 0.4596 0.00953 0.00367 -0.0544 0.7511 1.0000
1.750 0.4840 0.00954 0.00362 -0.0535 0.7383 1.0000
2.000 0.5086 0.00955 0.00358 -0.0525 0.7247 1.0000
2.250 0.5332 0.00958 0.00356 -0.0516 0.7101 1.0000
2.500 0.5580 0.00963 0.00355 -0.0507 0.6942 1.0000
2.750 0.5827 0.00968 0.00357 -0.0498 0.6776 1.0000
3.000 0.6075 0.00976 0.00358 -0.0490 0.6600 1.0000
3.250 0.6322 0.00986 0.00360 -0.0481 0.6414 1.0000
3.500 0.6569 0.00998 0.00368 -0.0473 0.6201 1.0000
3.750 0.6813 0.01013 0.00376 -0.0464 0.5986 1.0000
4.000 0.7057 0.01031 0.00388 -0.0456 0.5745 1.0000
4.250 0.7298 0.01052 0.00402 -0.0448 0.5489 1.0000
4.500 0.7537 0.01077 0.00418 -0.0439 0.5219 1.0000
4.750 0.7772 0.01106 0.00440 -0.0430 0.4930 1.0000
5.000 0.8004 0.01139 0.00463 -0.0422 0.4628 1.0000
5.250 0.8232 0.01177 0.00489 -0.0413 0.4318 1.0000
5.500 0.8457 0.01220 0.00520 -0.0403 0.4013 1.0000
5.750 0.8679 0.01266 0.00557 -0.0394 0.3720 1.0000
6.000 0.8900 0.01314 0.00596 -0.0385 0.3448 1.0000
6.250 0.9121 0.01364 0.00638 -0.0377 0.3197 1.0000
6.500 0.9338 0.01418 0.00683 -0.0368 0.2975 1.0000
6.750 0.9557 0.01470 0.00731 -0.0359 0.2759 1.0000
7.000 0.9768 0.01529 0.00784 -0.0350 0.2569 1.0000
7.250 0.9985 0.01581 0.00838 -0.0341 0.2376 1.0000
7.500 1.0195 0.01638 0.00893 -0.0332 0.2195 1.0000
7.750 1.0400 0.01699 0.00951 -0.0322 0.2028 1.0000
8.000 1.0598 0.01765 0.01014 -0.0311 0.1870 1.0000
8.250 1.0798 0.01824 0.01078 -0.0301 0.1703 1.0000
8.500 1.0995 0.01878 0.01135 -0.0291 0.1522 1.0000
8.750 1.1182 0.01939 0.01195 -0.0280 0.1355 1.0000
9.000 1.1361 0.02007 0.01261 -0.0268 0.1203 1.0000
9.250 1.1532 0.02080 0.01332 -0.0255 0.1057 1.0000
9.500 1.1708 0.02148 0.01407 -0.0243 0.0910 1.0000
9.750 1.1876 0.02221 0.01482 -0.0231 0.0725 1.0000
10.000 1.1947 0.02378 0.01616 -0.0207 0.0448 1.0000
10.250 1.1942 0.02565 0.01801 -0.0171 0.0305 1.0000
10.500 1.1902 0.02761 0.01999 -0.0135 0.0263 1.0000
10.750 1.1949 0.02910 0.02163 -0.0111 0.0246 1.0000
11.000 1.1980 0.03080 0.02345 -0.0089 0.0227 1.0000
11.250 1.2004 0.03264 0.02540 -0.0069 0.0216 1.0000
11.500 1.2005 0.03479 0.02763 -0.0051 0.0206 1.0000
11.750 1.2000 0.03720 0.03013 -0.0035 0.0200 1.0000
12.000 1.1986 0.04013 0.03315 -0.0018 0.0192 1.0000
12.250 1.2037 0.04206 0.03529 -0.0009 0.0184 1.0000
12.500 1.2069 0.04442 0.03782 0.0000 0.0178 1.0000
12.750 1.2085 0.04690 0.04046 0.0006 0.0170 1.0000
13.000 1.2099 0.04970 0.04343 0.0013 0.0169 1.0000
13.250 1.2090 0.05280 0.04671 0.0016 0.0165 1.0000
13.500 1.2066 0.05621 0.05031 0.0018 0.0164 1.0000
13.750 1.2019 0.05991 0.05421 0.0015 0.0162 1.0000
14.000 1.1952 0.06401 0.05851 0.0007 0.0160 1.0000
14.250 1.1861 0.06859 0.06330 -0.0005 0.0159 1.0000
14.500 1.1749 0.07371 0.06865 -0.0022 0.0160 1.0000
14.750 1.1611 0.07946 0.07462 -0.0046 0.0160 1.0000
15.000 1.1466 0.08564 0.08100 -0.0076 0.0159 1.0000
15.250 1.1269 0.09323 0.08885 -0.0118 0.0163 1.0000
15.500 1.1076 0.10120 0.09702 -0.0165 0.0164 1.0000
15.750 1.0856 0.11034 0.10636 -0.0221 0.0165 1.0000
16.000 1.0615 0.12052 0.11674 -0.0285 0.0169 1.0000
16.250 1.0362 0.13177 0.12815 -0.0357 0.0173 1.0000
16.500 1.0041 0.14575 0.14227 -0.0445 0.0178 1.0000
16.750 0.9702 0.16144 0.15799 -0.0536 0.0187 1.0000
17.000 0.9473 0.17479 0.17135 -0.0604 0.0193 1.0000
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Polar data table (+)
Polar graphs
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