CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il) Reynolds number: 500,000 Max Cl/Cd: 85.46 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cast102-il-500000.txt Download as CSV file: xf-cast102-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4922 0.09394 0.09158 -0.0524 1.0000 0.0188
-10.500 -0.5121 0.08946 0.08713 -0.0527 1.0000 0.0188
-10.250 -0.5337 0.08562 0.08328 -0.0526 0.9996 0.0188
-10.000 -0.5422 0.07867 0.07621 -0.0597 0.9969 0.0188
-9.750 -0.5524 0.07300 0.07041 -0.0650 0.9938 0.0188
-9.500 -0.5683 0.06674 0.06400 -0.0679 0.9884 0.0190
-9.250 -0.5624 0.06217 0.05940 -0.0703 0.9865 0.0192
-9.000 -0.5523 0.05856 0.05570 -0.0727 0.9850 0.0194
-8.750 -0.5459 0.05558 0.05263 -0.0732 0.9804 0.0197
-8.500 -0.5334 0.05241 0.04935 -0.0747 0.9778 0.0200
-8.250 -0.5182 0.04913 0.04590 -0.0762 0.9758 0.0206
-8.000 -0.5011 0.04573 0.04230 -0.0775 0.9739 0.0215
-7.750 -0.4847 0.04374 0.03970 -0.0757 0.9694 0.0236
-7.500 -0.4787 0.03852 0.03407 -0.0747 0.9647 0.0241
-7.250 -0.4586 0.03511 0.03066 -0.0755 0.9626 0.0246
-7.000 -0.4361 0.03305 0.02852 -0.0761 0.9607 0.0252
-6.750 -0.4124 0.03132 0.02667 -0.0766 0.9590 0.0262
-6.500 -0.3933 0.02987 0.02504 -0.0754 0.9551 0.0280
-6.250 -0.3683 0.03093 0.02564 -0.0739 0.9514 0.0300
-6.000 -0.3511 0.02562 0.02017 -0.0737 0.9487 0.0315
-5.750 -0.3259 0.02411 0.01859 -0.0739 0.9468 0.0327
-5.500 -0.2995 0.02292 0.01727 -0.0739 0.9451 0.0348
-5.250 -0.2752 0.02169 0.01569 -0.0733 0.9428 0.0396
-5.000 -0.2513 0.02035 0.01442 -0.0730 0.9395 0.0415
-4.750 -0.2211 0.01736 0.01105 -0.0715 0.9372 0.0269
-4.500 -0.1943 0.01634 0.00994 -0.0712 0.9350 0.0270
-4.250 -0.1679 0.01518 0.00869 -0.0707 0.9331 0.0260
-4.000 -0.1417 0.01438 0.00785 -0.0704 0.9313 0.0261
-3.750 -0.1155 0.01375 0.00721 -0.0702 0.9296 0.0266
-3.500 -0.0910 0.01327 0.00672 -0.0697 0.9270 0.0273
-3.250 -0.0667 0.01286 0.00629 -0.0693 0.9238 0.0282
-3.000 -0.0404 0.01260 0.00601 -0.0691 0.9213 0.0296
-2.750 -0.0146 0.01209 0.00547 -0.0690 0.9190 0.0307
-2.500 0.0120 0.01162 0.00498 -0.0690 0.9170 0.0326
-2.250 0.0398 0.01134 0.00469 -0.0691 0.9153 0.0350
-2.000 0.0681 0.01117 0.00449 -0.0693 0.9137 0.0381
-1.750 0.0943 0.01096 0.00431 -0.0692 0.9109 0.0520
-1.500 0.1108 0.00873 0.00413 -0.0687 0.9074 0.6536
-1.250 0.1384 0.00879 0.00422 -0.0686 0.9049 0.6831
-1.000 0.1666 0.00877 0.00423 -0.0684 0.9020 0.7021
-0.750 0.1954 0.00868 0.00412 -0.0682 0.8986 0.7155
-0.500 0.2212 0.00865 0.00410 -0.0676 0.8918 0.7266
-0.250 0.2489 0.00849 0.00395 -0.0672 0.8866 0.7348
0.000 0.2771 0.00837 0.00379 -0.0669 0.8812 0.7423
0.250 0.3040 0.00817 0.00358 -0.0665 0.8729 0.7464
0.500 0.3322 0.00798 0.00338 -0.0662 0.8661 0.7500
0.750 0.3596 0.00786 0.00326 -0.0660 0.8582 0.7541
1.000 0.3889 0.00777 0.00314 -0.0662 0.8534 0.7582
1.250 0.4164 0.00772 0.00313 -0.0662 0.8471 0.7619
1.500 0.4447 0.00762 0.00305 -0.0662 0.8404 0.7660
1.750 0.4726 0.00757 0.00302 -0.0662 0.8330 0.7707
2.000 0.5010 0.00751 0.00296 -0.0662 0.8253 0.7754
2.250 0.5281 0.00742 0.00293 -0.0660 0.8143 0.7796
2.500 0.5552 0.00734 0.00285 -0.0657 0.7982 0.7844
2.750 0.5825 0.00729 0.00278 -0.0654 0.7783 0.7897
3.000 0.6085 0.00727 0.00276 -0.0650 0.7504 0.7947
3.250 0.6324 0.00740 0.00271 -0.0639 0.6936 0.8004
3.500 0.6447 0.00829 0.00291 -0.0608 0.5496 0.8068
3.750 0.6574 0.00924 0.00333 -0.0580 0.4288 0.8128
4.000 0.6761 0.00991 0.00366 -0.0566 0.3547 0.8199
4.250 0.6972 0.01038 0.00394 -0.0555 0.3046 0.8266
4.500 0.7194 0.01079 0.00419 -0.0547 0.2641 0.8348
4.750 0.7418 0.01115 0.00445 -0.0539 0.2324 0.8429
5.250 0.7874 0.01179 0.00498 -0.0523 0.1873 0.8624
5.500 0.8101 0.01207 0.00525 -0.0515 0.1720 0.8739
5.750 0.8324 0.01233 0.00552 -0.0505 0.1583 0.8879
6.000 0.8535 0.01257 0.00578 -0.0493 0.1451 0.9058
6.250 0.8728 0.01276 0.00602 -0.0476 0.1344 0.9314
6.500 0.8966 0.01298 0.00627 -0.0469 0.1238 0.9771
6.750 0.9231 0.01331 0.00656 -0.0472 0.1121 1.0000
7.000 0.9478 0.01367 0.00686 -0.0470 0.0998 1.0000
7.250 0.9718 0.01405 0.00719 -0.0467 0.0847 1.0000
7.500 0.9930 0.01469 0.00766 -0.0459 0.0578 1.0000
7.750 1.0127 0.01548 0.00828 -0.0448 0.0393 1.0000
8.000 1.0336 0.01612 0.00892 -0.0438 0.0341 1.0000
8.250 1.0548 0.01671 0.00953 -0.0429 0.0314 1.0000
8.500 1.0733 0.01752 0.01036 -0.0415 0.0290 1.0000
8.750 1.0923 0.01819 0.01111 -0.0402 0.0278 1.0000
9.000 1.1106 0.01882 0.01181 -0.0388 0.0267 1.0000
9.250 1.1281 0.01952 0.01256 -0.0373 0.0256 1.0000
9.500 1.1445 0.02030 0.01339 -0.0356 0.0245 1.0000
9.750 1.1576 0.02137 0.01451 -0.0335 0.0234 1.0000
10.000 1.1677 0.02281 0.01603 -0.0310 0.0226 1.0000
10.250 1.1843 0.02361 0.01693 -0.0296 0.0222 1.0000
10.500 1.1998 0.02453 0.01794 -0.0279 0.0218 1.0000
10.750 1.2143 0.02555 0.01906 -0.0263 0.0213 1.0000
11.000 1.2282 0.02664 0.02025 -0.0246 0.0208 1.0000
11.250 1.2414 0.02779 0.02150 -0.0228 0.0203 1.0000
11.500 1.2539 0.02900 0.02280 -0.0210 0.0199 1.0000
11.750 1.2656 0.03023 0.02411 -0.0193 0.0194 1.0000
12.000 1.2760 0.03159 0.02554 -0.0175 0.0189 1.0000
12.250 1.2848 0.03335 0.02738 -0.0156 0.0184 1.0000
12.500 1.2914 0.03614 0.03033 -0.0136 0.0180 1.0000
12.750 1.2959 0.03839 0.03276 -0.0114 0.0178 1.0000
13.000 1.2999 0.03996 0.03451 -0.0092 0.0176 1.0000
13.250 1.3021 0.04183 0.03656 -0.0071 0.0174 1.0000
13.500 1.3023 0.04396 0.03888 -0.0050 0.0173 1.0000
13.750 1.3002 0.04636 0.04146 -0.0030 0.0171 1.0000
14.000 1.2958 0.04906 0.04436 -0.0012 0.0170 1.0000
14.250 1.2890 0.05208 0.04758 0.0004 0.0168 1.0000
14.500 1.2796 0.05549 0.05119 0.0016 0.0167 1.0000
14.750 1.2683 0.05929 0.05519 0.0024 0.0166 1.0000
15.000 1.2547 0.06356 0.05966 0.0025 0.0165 1.0000
15.250 1.2392 0.06846 0.06475 0.0018 0.0165 1.0000
15.500 1.2216 0.07413 0.07063 0.0001 0.0164 1.0000
15.750 1.2018 0.08082 0.07752 -0.0029 0.0164 1.0000
16.000 1.1798 0.08870 0.08560 -0.0072 0.0164 1.0000
16.250 1.1549 0.09796 0.09506 -0.0129 0.0165 1.0000
16.500 1.1242 0.10917 0.10648 -0.0201 0.0167 1.0000
16.750 1.0886 0.12222 0.11972 -0.0285 0.0170 1.0000
17.000 1.0443 0.13802 0.13569 -0.0384 0.0174 1.0000
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