CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il) Reynolds number: 200,000 Max Cl/Cd: 55.59 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cast102-il-200000-n5.txt Download as CSV file: xf-cast102-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4988 0.09187 0.08825 -0.0467 1.0000 0.0266
-9.750 -0.5175 0.08736 0.08380 -0.0475 1.0000 0.0264
-9.500 -0.5326 0.08091 0.07732 -0.0526 0.9974 0.0262
-9.250 -0.5440 0.07441 0.07072 -0.0588 0.9921 0.0260
-9.000 -0.5531 0.06930 0.06547 -0.0625 0.9860 0.0260
-8.750 -0.5542 0.06503 0.06104 -0.0643 0.9805 0.0264
-8.500 -0.5503 0.06099 0.05680 -0.0658 0.9762 0.0275
-8.250 -0.4927 0.04002 0.03560 -0.0697 0.9652 0.0229
-7.750 -0.5361 0.04291 0.03720 -0.0648 0.9626 0.0187
-7.500 -0.5176 0.03975 0.03380 -0.0652 0.9605 0.0185
-7.250 -0.4968 0.03660 0.03031 -0.0655 0.9588 0.0184
-7.000 -0.4831 0.03414 0.02753 -0.0638 0.9539 0.0184
-6.750 -0.4626 0.03164 0.02466 -0.0631 0.9506 0.0185
-6.500 -0.4384 0.02937 0.02200 -0.0630 0.9483 0.0187
-6.250 -0.4129 0.02740 0.01980 -0.0633 0.9465 0.0193
-6.000 -0.3853 0.02634 0.01869 -0.0641 0.9451 0.0202
-5.750 -0.3566 0.02503 0.01719 -0.0647 0.9439 0.0211
-5.500 -0.3369 0.02380 0.01577 -0.0632 0.9396 0.0213
-5.250 -0.3115 0.02255 0.01435 -0.0628 0.9368 0.0216
-5.000 -0.2843 0.02144 0.01307 -0.0627 0.9347 0.0221
-4.750 -0.2564 0.02046 0.01198 -0.0628 0.9330 0.0226
-4.500 -0.2280 0.01962 0.01104 -0.0630 0.9314 0.0232
-4.250 -0.1999 0.01875 0.01017 -0.0634 0.9300 0.0245
-4.000 -0.1731 0.01810 0.00954 -0.0636 0.9282 0.0260
-3.750 -0.1545 0.01764 0.00907 -0.0620 0.9237 0.0268
-3.500 -0.1306 0.01710 0.00853 -0.0615 0.9209 0.0277
-3.250 -0.1046 0.01660 0.00799 -0.0615 0.9186 0.0288
-3.000 -0.0768 0.01616 0.00750 -0.0618 0.9167 0.0299
-2.750 -0.0485 0.01562 0.00696 -0.0623 0.9151 0.0330
-2.500 -0.0189 0.01529 0.00658 -0.0630 0.9137 0.0362
-2.250 0.0012 0.01518 0.00642 -0.0617 0.9094 0.0389
-2.000 0.0261 0.01497 0.00620 -0.0614 0.9062 0.0458
-1.750 0.0438 0.01260 0.00584 -0.0613 0.9035 0.5654
-1.500 0.0702 0.01258 0.00609 -0.0607 0.9016 0.6649
-1.250 0.0984 0.01268 0.00623 -0.0606 0.9000 0.6980
-1.000 0.1275 0.01275 0.00634 -0.0606 0.8986 0.7184
-0.750 0.1484 0.01297 0.00659 -0.0592 0.8941 0.7343
-0.500 0.1740 0.01309 0.00668 -0.0589 0.8908 0.7445
-0.250 0.2024 0.01310 0.00669 -0.0591 0.8883 0.7476
0.000 0.2333 0.01304 0.00661 -0.0598 0.8859 0.7511
0.250 0.2677 0.01280 0.00634 -0.0609 0.8826 0.7553
0.500 0.2923 0.01265 0.00618 -0.0600 0.8728 0.7600
0.750 0.3245 0.01228 0.00582 -0.0604 0.8659 0.7634
1.000 0.3521 0.01201 0.00555 -0.0599 0.8558 0.7675
1.250 0.3793 0.01175 0.00530 -0.0594 0.8442 0.7722
1.500 0.4075 0.01151 0.00506 -0.0591 0.8330 0.7767
1.750 0.4364 0.01129 0.00487 -0.0590 0.8232 0.7811
2.000 0.4616 0.01125 0.00487 -0.0584 0.8117 0.7865
2.250 0.4884 0.01118 0.00485 -0.0580 0.8001 0.7917
2.500 0.5147 0.01108 0.00481 -0.0576 0.7863 0.7963
2.750 0.5415 0.01097 0.00474 -0.0571 0.7673 0.8021
3.000 0.5684 0.01086 0.00463 -0.0567 0.7395 0.8080
3.250 0.5965 0.01073 0.00436 -0.0561 0.6797 0.8137
3.500 0.6135 0.01134 0.00420 -0.0534 0.5373 0.8207
3.750 0.6253 0.01222 0.00456 -0.0504 0.4334 0.8273
4.000 0.6416 0.01289 0.00493 -0.0484 0.3678 0.8353
4.250 0.6603 0.01339 0.00527 -0.0468 0.3227 0.8434
4.500 0.6807 0.01383 0.00559 -0.0456 0.2872 0.8530
4.750 0.7010 0.01421 0.00590 -0.0444 0.2596 0.8631
5.000 0.7221 0.01456 0.00621 -0.0432 0.2368 0.8744
5.250 0.7427 0.01492 0.00656 -0.0420 0.2166 0.8877
5.500 0.7630 0.01527 0.00688 -0.0407 0.1980 0.9044
5.750 0.7841 0.01561 0.00721 -0.0395 0.1809 0.9261
6.000 0.8090 0.01597 0.00758 -0.0393 0.1649 0.9568
6.250 0.8354 0.01635 0.00793 -0.0395 0.1513 1.0000
6.500 0.8585 0.01679 0.00833 -0.0391 0.1385 1.0000
6.750 0.8813 0.01724 0.00873 -0.0387 0.1251 1.0000
7.000 0.9042 0.01769 0.00918 -0.0382 0.1138 1.0000
7.250 0.9271 0.01812 0.00962 -0.0376 0.1026 1.0000
7.500 0.9493 0.01861 0.01008 -0.0370 0.0896 1.0000
7.750 0.9707 0.01917 0.01061 -0.0363 0.0755 1.0000
8.000 0.9914 0.01981 0.01121 -0.0355 0.0598 1.0000
8.250 1.0105 0.02059 0.01190 -0.0344 0.0453 1.0000
8.500 1.0289 0.02138 0.01266 -0.0332 0.0382 1.0000
8.750 1.0467 0.02220 0.01350 -0.0318 0.0345 1.0000
9.000 1.0646 0.02297 0.01437 -0.0305 0.0322 1.0000
9.250 1.0814 0.02383 0.01529 -0.0290 0.0302 1.0000
9.500 1.0955 0.02488 0.01638 -0.0273 0.0285 1.0000
9.750 1.1118 0.02574 0.01738 -0.0258 0.0272 1.0000
10.000 1.1268 0.02669 0.01844 -0.0242 0.0259 1.0000
10.250 1.1406 0.02773 0.01958 -0.0226 0.0250 1.0000
10.500 1.1532 0.02886 0.02081 -0.0208 0.0242 1.0000
10.750 1.1640 0.03014 0.02217 -0.0189 0.0235 1.0000
11.000 1.1724 0.03167 0.02376 -0.0168 0.0229 1.0000
11.250 1.1827 0.03310 0.02533 -0.0149 0.0224 1.0000
11.500 1.1937 0.03446 0.02685 -0.0132 0.0219 1.0000
11.750 1.2036 0.03592 0.02847 -0.0115 0.0213 1.0000
12.000 1.2123 0.03746 0.03017 -0.0098 0.0206 1.0000
12.250 1.2197 0.03910 0.03196 -0.0081 0.0201 1.0000
12.500 1.2259 0.04085 0.03385 -0.0064 0.0196 1.0000
12.750 1.2307 0.04276 0.03591 -0.0047 0.0192 1.0000
13.000 1.2342 0.04481 0.03809 -0.0031 0.0189 1.0000
13.250 1.2363 0.04704 0.04045 -0.0015 0.0186 1.0000
13.500 1.2369 0.04949 0.04303 -0.0001 0.0183 1.0000
13.750 1.2357 0.05224 0.04592 0.0012 0.0181 1.0000
14.000 1.2317 0.05542 0.04926 0.0024 0.0179 1.0000
14.250 1.2254 0.05874 0.05280 0.0033 0.0178 1.0000
14.500 1.2168 0.06242 0.05672 0.0037 0.0176 1.0000
14.750 1.2059 0.06659 0.06113 0.0035 0.0175 1.0000
15.000 1.1929 0.07134 0.06612 0.0026 0.0174 1.0000
15.250 1.1779 0.07679 0.07181 0.0008 0.0174 1.0000
15.500 1.1611 0.08309 0.07834 -0.0020 0.0173 1.0000
15.750 1.1426 0.09035 0.08582 -0.0060 0.0173 1.0000
16.000 1.1223 0.09860 0.09429 -0.0110 0.0173 1.0000
16.250 1.1002 0.10779 0.10368 -0.0168 0.0174 1.0000
16.500 1.0755 0.11810 0.11419 -0.0235 0.0174 1.0000
16.750 1.0477 0.12956 0.12581 -0.0308 0.0176 1.0000
17.000 1.0157 0.14269 0.13910 -0.0390 0.0177 1.0000
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