WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il) Reynolds number: 200,000 Max Cl/Cd: 68.83 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-wb13535sm-il-200000-n5.txt Download as CSV file: xf-wb13535sm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WB-135/35 13.5% smoothed
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4269 0.10537 0.10174 -0.0473 1.0000 0.0137
-12.500 -0.4932 0.08622 0.08249 -0.0568 1.0000 0.0129
-12.250 -0.5427 0.07329 0.06939 -0.0646 1.0000 0.0122
-12.000 -0.5615 0.06700 0.06302 -0.0684 1.0000 0.0124
-11.750 -0.5887 0.05971 0.05557 -0.0728 1.0000 0.0120
-11.500 -0.6076 0.05432 0.05007 -0.0760 1.0000 0.0120
-11.250 -0.6244 0.04983 0.04549 -0.0784 1.0000 0.0120
-11.000 -0.6490 0.04542 0.04095 -0.0799 1.0000 0.0118
-10.750 -0.6636 0.04251 0.03793 -0.0812 0.9969 0.0119
-10.500 -0.6529 0.03877 0.03390 -0.0856 0.9852 0.0121
-10.250 -0.6364 0.03589 0.03076 -0.0885 0.9754 0.0125
-10.000 -0.6196 0.03332 0.02793 -0.0901 0.9658 0.0128
-9.750 -0.5994 0.03107 0.02540 -0.0915 0.9574 0.0132
-9.500 -0.5748 0.02899 0.02308 -0.0932 0.9507 0.0137
-9.250 -0.5522 0.02725 0.02114 -0.0938 0.9419 0.0140
-9.000 -0.5245 0.02565 0.01932 -0.0952 0.9356 0.0147
-8.750 -0.4991 0.02455 0.01803 -0.0957 0.9269 0.0154
-8.500 -0.4747 0.02275 0.01615 -0.0966 0.9198 0.0166
-8.250 -0.4517 0.02170 0.01500 -0.0966 0.9100 0.0176
-8.000 -0.4260 0.02065 0.01380 -0.0969 0.9019 0.0185
-7.750 -0.4024 0.01972 0.01272 -0.0967 0.8924 0.0197
-7.500 -0.3789 0.01894 0.01178 -0.0962 0.8832 0.0210
-7.250 -0.3553 0.01803 0.01073 -0.0960 0.8749 0.0233
-7.000 -0.3330 0.01736 0.00994 -0.0952 0.8649 0.0258
-6.750 -0.3083 0.01676 0.00915 -0.0948 0.8564 0.0286
-6.500 -0.2854 0.01602 0.00831 -0.0941 0.8474 0.0342
-6.250 -0.2624 0.01530 0.00752 -0.0933 0.8389 0.0463
-6.000 -0.2415 0.01425 0.00675 -0.0926 0.8311 0.1024
-5.750 -0.2172 0.01384 0.00645 -0.0921 0.8230 0.1479
-5.500 -0.1903 0.01364 0.00619 -0.0919 0.8159 0.1705
-5.250 -0.1646 0.01348 0.00601 -0.0915 0.8081 0.1902
-5.000 -0.1378 0.01336 0.00581 -0.0913 0.8015 0.2093
-4.750 -0.1117 0.01324 0.00564 -0.0909 0.7949 0.2233
-4.500 -0.0851 0.01309 0.00542 -0.0906 0.7884 0.2325
-4.250 -0.0581 0.01296 0.00518 -0.0903 0.7825 0.2406
-4.000 -0.0321 0.01282 0.00500 -0.0899 0.7758 0.2482
-3.750 -0.0047 0.01271 0.00479 -0.0897 0.7705 0.2568
-3.500 0.0215 0.01259 0.00465 -0.0894 0.7647 0.2648
-3.250 0.0482 0.01250 0.00450 -0.0891 0.7589 0.2747
-3.000 0.0756 0.01243 0.00436 -0.0889 0.7542 0.2859
-2.750 0.1014 0.01235 0.00428 -0.0885 0.7475 0.2964
-2.500 0.1284 0.01228 0.00414 -0.0882 0.7409 0.3073
-2.250 0.1542 0.01222 0.00404 -0.0877 0.7323 0.3192
-2.000 0.1809 0.01215 0.00391 -0.0873 0.7244 0.3318
-1.750 0.2063 0.01208 0.00386 -0.0867 0.7159 0.3439
-1.500 0.2331 0.01203 0.00377 -0.0864 0.7095 0.3562
-1.250 0.2588 0.01199 0.00373 -0.0859 0.7020 0.3684
-1.000 0.2854 0.01195 0.00367 -0.0856 0.6955 0.3821
-0.750 0.3111 0.01191 0.00365 -0.0851 0.6878 0.3966
-0.500 0.3372 0.01187 0.00361 -0.0846 0.6801 0.4118
-0.250 0.3627 0.01184 0.00361 -0.0841 0.6722 0.4271
0.000 0.3889 0.01181 0.00361 -0.0836 0.6661 0.4441
0.250 0.4146 0.01179 0.00364 -0.0832 0.6598 0.4621
0.500 0.4403 0.01177 0.00367 -0.0827 0.6528 0.4815
0.750 0.4660 0.01175 0.00369 -0.0821 0.6458 0.5020
1.000 0.4911 0.01172 0.00373 -0.0815 0.6380 0.5232
1.250 0.5164 0.01170 0.00377 -0.0809 0.6305 0.5464
1.500 0.5412 0.01166 0.00382 -0.0803 0.6225 0.5713
1.750 0.5657 0.01160 0.00387 -0.0795 0.6142 0.6014
2.250 0.6137 0.01126 0.00398 -0.0777 0.5941 0.7190
2.750 0.7382 0.01114 0.00423 -0.0924 0.5613 1.0000
3.000 0.7605 0.01128 0.00432 -0.0912 0.5452 1.0000
3.250 0.7821 0.01144 0.00441 -0.0899 0.5252 1.0000
3.500 0.8023 0.01166 0.00450 -0.0884 0.4999 1.0000
3.750 0.8211 0.01193 0.00464 -0.0866 0.4708 1.0000
4.000 0.8389 0.01227 0.00482 -0.0846 0.4426 1.0000
4.250 0.8565 0.01265 0.00505 -0.0827 0.4180 1.0000
4.500 0.8740 0.01305 0.00532 -0.0808 0.3978 1.0000
4.750 0.8919 0.01344 0.00563 -0.0790 0.3817 1.0000
5.000 0.9105 0.01382 0.00594 -0.0773 0.3682 1.0000
5.250 0.9295 0.01419 0.00626 -0.0757 0.3567 1.0000
5.500 0.9486 0.01456 0.00659 -0.0742 0.3473 1.0000
5.750 0.9679 0.01492 0.00694 -0.0727 0.3386 1.0000
6.000 0.9874 0.01527 0.00729 -0.0713 0.3307 1.0000
6.250 1.0046 0.01570 0.00766 -0.0695 0.3196 1.0000
6.500 1.0217 0.01609 0.00802 -0.0676 0.3068 1.0000
6.750 1.0394 0.01645 0.00841 -0.0660 0.2957 1.0000
7.000 1.0563 0.01684 0.00879 -0.0641 0.2862 1.0000
7.250 1.0714 0.01724 0.00918 -0.0620 0.2767 1.0000
7.500 1.0871 0.01760 0.00958 -0.0599 0.2660 1.0000
7.750 1.1007 0.01803 0.01001 -0.0576 0.2524 1.0000
8.000 1.1124 0.01855 0.01047 -0.0551 0.2329 1.0000
8.250 1.1250 0.01910 0.01100 -0.0528 0.2120 1.0000
8.500 1.1321 0.01996 0.01167 -0.0499 0.1772 1.0000
8.750 1.1332 0.02128 0.01269 -0.0465 0.1348 1.0000
9.000 1.1118 0.02420 0.01494 -0.0409 0.0404 1.0000
9.250 1.1116 0.02591 0.01651 -0.0380 0.0216 1.0000
9.500 1.1205 0.02707 0.01774 -0.0360 0.0190 1.0000
9.750 1.1307 0.02815 0.01894 -0.0343 0.0178 1.0000
10.000 1.1399 0.02934 0.02026 -0.0327 0.0170 1.0000
10.250 1.1476 0.03069 0.02174 -0.0310 0.0159 1.0000
10.500 1.1538 0.03220 0.02338 -0.0294 0.0151 1.0000
10.750 1.1580 0.03392 0.02523 -0.0279 0.0144 1.0000
11.000 1.1586 0.03601 0.02749 -0.0263 0.0137 1.0000
11.250 1.1562 0.03846 0.03009 -0.0248 0.0132 1.0000
11.500 1.1530 0.04108 0.03285 -0.0236 0.0129 1.0000
11.750 1.1536 0.04344 0.03533 -0.0226 0.0127 1.0000
12.000 1.1524 0.04606 0.03809 -0.0219 0.0124 1.0000
12.250 1.1507 0.04883 0.04097 -0.0213 0.0123 1.0000
12.500 1.1492 0.05168 0.04394 -0.0208 0.0121 1.0000
12.750 1.1474 0.05468 0.04705 -0.0206 0.0115 1.0000
13.000 1.1431 0.05806 0.05054 -0.0204 0.0114 1.0000
13.250 1.1401 0.06139 0.05397 -0.0205 0.0111 1.0000
13.500 1.1379 0.06473 0.05741 -0.0207 0.0107 1.0000
13.750 1.1354 0.06819 0.06097 -0.0210 0.0105 1.0000
14.000 1.1320 0.07182 0.06467 -0.0214 0.0101 1.0000
14.250 1.1306 0.07521 0.06815 -0.0218 0.0100 1.0000
14.500 1.1288 0.07869 0.07170 -0.0222 0.0098 1.0000
14.750 1.1292 0.08186 0.07494 -0.0224 0.0097 1.0000
15.000 1.1297 0.08492 0.07803 -0.0226 0.0095 1.0000
15.250 1.1328 0.08756 0.08071 -0.0225 0.0094 1.0000
15.500 1.1403 0.08915 0.08226 -0.0212 0.0091 1.0000
15.750 1.1444 0.09191 0.08513 -0.0215 0.0090 1.0000
16.000 1.1476 0.09486 0.08821 -0.0219 0.0089 1.0000
16.250 1.1510 0.09777 0.09123 -0.0222 0.0088 1.0000
16.500 1.1544 0.10070 0.09428 -0.0225 0.0088 1.0000
16.750 1.1556 0.10409 0.09781 -0.0233 0.0087 1.0000
17.000 1.1554 0.10779 0.10167 -0.0244 0.0085 1.0000
17.250 1.1538 0.11183 0.10587 -0.0258 0.0084 1.0000
17.500 1.1507 0.11621 0.11041 -0.0277 0.0082 1.0000
17.750 1.1485 0.12039 0.11477 -0.0292 0.0081 1.0000
18.000 1.1434 0.12528 0.11982 -0.0316 0.0078 1.0000
18.250 1.1394 0.12998 0.12468 -0.0338 0.0079 1.0000
18.500 1.1343 0.13503 0.12987 -0.0365 0.0076 1.0000
18.750 1.1285 0.14028 0.13527 -0.0393 0.0075 1.0000
19.000 1.1228 0.14562 0.14075 -0.0423 0.0074 1.0000
19.250 1.1156 0.15136 0.14665 -0.0456 0.0073 1.0000
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Polar data table (+)
Polar graphs
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