CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il) Reynolds number: 100,000 Max Cl/Cd: 42.98 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cast102-il-100000-n5.txt Download as CSV file: xf-cast102-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CAST 10-2/DOA 2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4169 0.09431 0.08968 -0.0390 1.0000 0.0676
-9.500 -0.4303 0.09026 0.08568 -0.0393 1.0000 0.0685
-9.250 -0.4474 0.08574 0.08120 -0.0401 1.0000 0.0691
-9.000 -0.4694 0.08080 0.07631 -0.0413 1.0000 0.0693
-8.750 -0.4950 0.07644 0.07196 -0.0414 1.0000 0.0693
-8.500 -0.5227 0.07266 0.06818 -0.0405 0.9997 0.0690
-8.250 -0.5450 0.06789 0.06333 -0.0417 0.9954 0.0691
-7.750 -0.5805 0.05776 0.05266 -0.0436 0.9851 0.0745
-7.500 -0.5733 0.05353 0.04838 -0.0433 0.9821 0.0756
-7.000 -0.6090 0.05074 0.04347 -0.0370 0.9829 0.0300
-6.750 -0.5924 0.04733 0.03985 -0.0369 0.9799 0.0297
-6.500 -0.5739 0.04412 0.03621 -0.0369 0.9769 0.0304
-6.250 -0.5525 0.04167 0.03377 -0.0377 0.9750 0.0316
-6.000 -0.5282 0.03926 0.03105 -0.0381 0.9732 0.0322
-5.750 -0.5063 0.03673 0.02806 -0.0373 0.9705 0.0316
-5.500 -0.4829 0.03454 0.02543 -0.0367 0.9677 0.0312
-5.250 -0.4570 0.03264 0.02318 -0.0365 0.9653 0.0312
-5.000 -0.4301 0.03098 0.02126 -0.0366 0.9635 0.0313
-4.750 -0.4020 0.02951 0.01959 -0.0368 0.9619 0.0317
-4.500 -0.3729 0.02834 0.01833 -0.0374 0.9604 0.0332
-4.250 -0.3424 0.02731 0.01715 -0.0381 0.9590 0.0352
-4.000 -0.3176 0.02636 0.01607 -0.0375 0.9564 0.0361
-3.750 -0.2935 0.02547 0.01511 -0.0369 0.9539 0.0368
-3.500 -0.2682 0.02470 0.01427 -0.0365 0.9516 0.0375
-3.250 -0.2419 0.02383 0.01343 -0.0365 0.9495 0.0386
-3.000 -0.2146 0.02309 0.01276 -0.0370 0.9474 0.0415
-2.750 -0.1853 0.02260 0.01222 -0.0377 0.9456 0.0449
-2.500 -0.1549 0.02219 0.01168 -0.0386 0.9441 0.0474
-2.250 -0.1330 0.02180 0.01123 -0.0378 0.9407 0.0507
-2.000 -0.1076 0.02153 0.01090 -0.0377 0.9374 0.0578
-1.750 -0.0794 0.02112 0.01056 -0.0383 0.9349 0.0794
-1.500 -0.0592 0.01900 0.01093 -0.0377 0.9336 0.6737
-1.250 -0.0358 0.01940 0.01146 -0.0358 0.9309 0.7415
-1.000 -0.0095 0.01972 0.01178 -0.0347 0.9288 0.7747
-0.750 0.0026 0.01998 0.01209 -0.0309 0.9235 0.7969
-0.500 0.0261 0.02013 0.01220 -0.0299 0.9198 0.8113
-0.250 0.0569 0.02020 0.01218 -0.0309 0.9169 0.8164
0.000 0.0909 0.02026 0.01216 -0.0326 0.9146 0.8219
0.250 0.1144 0.02037 0.01226 -0.0320 0.9101 0.8268
0.500 0.1401 0.02047 0.01233 -0.0320 0.9053 0.8325
0.750 0.1715 0.02055 0.01239 -0.0331 0.9018 0.8384
1.250 0.2312 0.02052 0.01238 -0.0341 0.8892 0.8508
1.500 0.2713 0.02010 0.01197 -0.0359 0.8792 0.8558
1.750 0.3161 0.01949 0.01139 -0.0384 0.8689 0.8610
2.000 0.3444 0.01918 0.01113 -0.0381 0.8570 0.8687
2.250 0.3750 0.01884 0.01086 -0.0381 0.8472 0.8757
2.500 0.4135 0.01826 0.01034 -0.0395 0.8387 0.8832
2.750 0.4379 0.01796 0.01014 -0.0383 0.8259 0.8917
3.000 0.4640 0.01763 0.00990 -0.0374 0.8127 0.9018
3.250 0.4903 0.01728 0.00966 -0.0366 0.7981 0.9134
3.500 0.5173 0.01694 0.00944 -0.0359 0.7814 0.9259
3.750 0.5431 0.01671 0.00934 -0.0352 0.7590 0.9413
4.000 0.5724 0.01644 0.00918 -0.0351 0.7282 0.9596
4.250 0.6146 0.01578 0.00849 -0.0369 0.6678 0.9744
4.500 0.6654 0.01548 0.00729 -0.0395 0.5037 0.9766
4.750 0.6865 0.01634 0.00757 -0.0387 0.4057 1.0000
5.000 0.7038 0.01706 0.00795 -0.0373 0.3507 1.0000
5.250 0.7237 0.01772 0.00839 -0.0364 0.3090 1.0000
5.500 0.7447 0.01833 0.00884 -0.0357 0.2770 1.0000
5.750 0.7665 0.01892 0.00931 -0.0350 0.2511 1.0000
6.000 0.7883 0.01952 0.00982 -0.0343 0.2312 1.0000
6.250 0.8103 0.02013 0.01040 -0.0337 0.2152 1.0000
6.500 0.8323 0.02075 0.01098 -0.0331 0.2004 1.0000
6.750 0.8540 0.02137 0.01158 -0.0324 0.1855 1.0000
7.000 0.8753 0.02199 0.01218 -0.0317 0.1702 1.0000
7.250 0.8966 0.02256 0.01275 -0.0310 0.1530 1.0000
7.500 0.9176 0.02314 0.01334 -0.0303 0.1366 1.0000
7.750 0.9384 0.02376 0.01399 -0.0295 0.1231 1.0000
8.000 0.9589 0.02441 0.01470 -0.0287 0.1092 1.0000
8.250 0.9789 0.02512 0.01546 -0.0278 0.0947 1.0000
8.500 0.9977 0.02595 0.01630 -0.0267 0.0791 1.0000
8.750 1.0143 0.02695 0.01727 -0.0254 0.0660 1.0000
9.000 1.0298 0.02806 0.01842 -0.0238 0.0573 1.0000
9.250 1.0436 0.02927 0.01962 -0.0220 0.0521 1.0000
9.500 1.0587 0.03043 0.02091 -0.0204 0.0476 1.0000
9.750 1.0717 0.03164 0.02217 -0.0187 0.0442 1.0000
10.000 1.0847 0.03300 0.02365 -0.0170 0.0417 1.0000
10.250 1.0977 0.03442 0.02525 -0.0152 0.0398 1.0000
10.500 1.1098 0.03590 0.02686 -0.0135 0.0383 1.0000
10.750 1.1206 0.03743 0.02850 -0.0118 0.0369 1.0000
11.000 1.1296 0.03919 0.03032 -0.0100 0.0357 1.0000
11.250 1.1401 0.04102 0.03237 -0.0083 0.0344 1.0000
11.750 1.1557 0.04494 0.03680 -0.0048 0.0321 1.0000
12.000 1.1608 0.04715 0.03923 -0.0029 0.0313 1.0000
12.250 1.1638 0.04951 0.04181 -0.0011 0.0307 1.0000
12.500 1.1648 0.05203 0.04453 0.0006 0.0302 1.0000
12.750 1.1635 0.05475 0.04745 0.0023 0.0298 1.0000
13.000 1.1601 0.05771 0.05061 0.0038 0.0294 1.0000
13.250 1.1545 0.06094 0.05405 0.0050 0.0291 1.0000
13.500 1.1464 0.06452 0.05782 0.0059 0.0288 1.0000
13.750 1.1356 0.06858 0.06207 0.0064 0.0286 1.0000
14.000 1.1192 0.07336 0.06709 0.0062 0.0285 1.0000
14.250 1.0994 0.07893 0.07294 0.0049 0.0284 1.0000
14.500 1.0777 0.08537 0.07962 0.0023 0.0284 1.0000
14.750 1.0542 0.09291 0.08739 -0.0017 0.0285 1.0000
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Polar data table (+)
Polar graphs
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