DU 06-W-200 VAWT airfoil (du06-w-200-dt) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: DU 06-W-200 VAWT airfoil (du06-w-200-dt) Reynolds number: 100,000 Max Cl/Cd: 32.73 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du06-w-200-dt-100000.txt Download as CSV file: xf-du06-w-200-dt-100000.csv |
XFOIL Version 6.96
Calculated polar for: DU 06-W-200 VAWT 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9910 0.10177 0.09620 -0.0140 1.0000 0.1114
-16.500 -1.0713 0.08625 0.08031 -0.0219 1.0000 0.1102
-16.250 -1.1211 0.07710 0.07082 -0.0256 1.0000 0.1105
-16.000 -1.1598 0.07034 0.06372 -0.0275 1.0000 0.1114
-15.750 -1.1344 0.06982 0.06338 -0.0267 1.0000 0.1165
-15.500 -1.1428 0.06641 0.05987 -0.0272 1.0000 0.1198
-15.250 -1.1642 0.06192 0.05512 -0.0277 1.0000 0.1225
-15.000 -1.1884 0.05757 0.05044 -0.0277 1.0000 0.1248
-14.750 -1.1697 0.05626 0.04927 -0.0273 1.0000 0.1302
-14.500 -1.1694 0.05408 0.04702 -0.0269 1.0000 0.1348
-14.250 -1.1848 0.05082 0.04348 -0.0264 1.0000 0.1384
-14.000 -1.1735 0.04906 0.04176 -0.0259 1.0000 0.1439
-13.750 -1.1659 0.04755 0.04024 -0.0253 1.0000 0.1495
-13.500 -1.1781 0.04491 0.03730 -0.0243 1.0000 0.1539
-13.250 -1.1560 0.04387 0.03642 -0.0239 1.0000 0.1608
-13.000 -1.1549 0.04210 0.03453 -0.0230 1.0000 0.1668
-12.750 -1.1501 0.04029 0.03261 -0.0220 1.0000 0.1728
-12.500 -1.1341 0.03929 0.03170 -0.0214 1.0000 0.1801
-12.250 -1.1419 0.03750 0.02959 -0.0195 1.0000 0.1857
-12.000 -1.1136 0.03665 0.02901 -0.0196 1.0000 0.1944
-11.750 -1.1145 0.03518 0.02727 -0.0179 1.0000 0.2014
-11.500 -1.0890 0.03433 0.02664 -0.0177 1.0000 0.2103
-11.250 -1.0831 0.03299 0.02507 -0.0164 1.0000 0.2186
-11.000 -1.0590 0.03219 0.02447 -0.0161 1.0000 0.2280
-10.750 -1.0444 0.03106 0.02328 -0.0153 1.0000 0.2374
-10.500 -1.0271 0.03017 0.02241 -0.0146 1.0000 0.2476
-10.250 -1.0065 0.02928 0.02161 -0.0140 1.0000 0.2577
-10.000 -0.9917 0.02829 0.02054 -0.0132 1.0000 0.2688
-9.750 -0.9709 0.02755 0.01991 -0.0126 1.0000 0.2802
-9.500 -0.9507 0.02678 0.01925 -0.0120 1.0000 0.2918
-9.250 -0.9338 0.02598 0.01847 -0.0111 1.0000 0.3041
-9.000 -0.9201 0.02528 0.01776 -0.0098 1.0000 0.3171
-8.750 -0.9058 0.02482 0.01752 -0.0082 1.0000 0.3288
-8.500 -0.9048 0.02443 0.01720 -0.0049 1.0000 0.3390
-8.250 -0.9073 0.02409 0.01686 -0.0016 1.0000 0.3500
-8.000 -0.8596 0.02352 0.01639 -0.0062 0.9885 0.3705
-7.750 -0.8079 0.02307 0.01607 -0.0112 0.9770 0.3923
-7.500 -0.7570 0.02258 0.01561 -0.0161 0.9652 0.4161
-7.250 -0.7116 0.02221 0.01531 -0.0196 0.9509 0.4380
-7.000 -0.6693 0.02211 0.01533 -0.0219 0.9355 0.4583
-6.750 -0.6321 0.02212 0.01541 -0.0230 0.9188 0.4773
-6.500 -0.5999 0.02231 0.01565 -0.0228 0.9015 0.4947
-6.250 -0.5707 0.02267 0.01605 -0.0218 0.8844 0.5101
-6.000 -0.5434 0.02316 0.01652 -0.0205 0.8677 0.5245
-5.750 -0.5180 0.02363 0.01695 -0.0190 0.8514 0.5385
-5.500 -0.4854 0.02509 0.01843 -0.0169 0.8363 0.5449
-5.250 -0.4603 0.02573 0.01899 -0.0152 0.8218 0.5565
-5.000 -0.4290 0.02718 0.02039 -0.0130 0.8094 0.5618
-4.750 -0.4041 0.02775 0.02088 -0.0118 0.7955 0.5728
-4.500 -0.3723 0.02919 0.02228 -0.0099 0.7825 0.5773
-4.250 -0.3490 0.02957 0.02254 -0.0087 0.7715 0.5888
-4.000 -0.3174 0.03087 0.02379 -0.0069 0.7602 0.5929
-3.750 -0.2946 0.03104 0.02388 -0.0063 0.7496 0.6049
-3.500 -0.2638 0.03211 0.02487 -0.0044 0.7406 0.6092
-3.250 -0.2412 0.03218 0.02489 -0.0040 0.7300 0.6212
-3.000 -0.2111 0.03304 0.02566 -0.0022 0.7224 0.6262
-2.750 -0.1888 0.03302 0.02562 -0.0021 0.7125 0.6379
-2.500 -0.1593 0.03364 0.02616 -0.0005 0.7053 0.6434
-2.250 -0.1375 0.03359 0.02609 -0.0003 0.6962 0.6549
-2.000 -0.1085 0.03404 0.02647 0.0011 0.6891 0.6612
-1.750 -0.0869 0.03396 0.02637 0.0015 0.6812 0.6721
-1.500 -0.0684 0.03367 0.02601 0.0017 0.6738 0.6859
-1.250 -0.0375 0.03407 0.02638 0.0033 0.6675 0.6895
-1.000 -0.0186 0.03392 0.02622 0.0034 0.6592 0.7025
-0.750 0.0114 0.03406 0.02631 0.0048 0.6531 0.7071
-0.500 0.0286 0.03391 0.02616 0.0050 0.6455 0.7202
-0.250 0.0590 0.03402 0.02626 0.0062 0.6384 0.7247
0.000 0.0766 0.03369 0.02584 0.0069 0.6332 0.7372
0.250 0.1055 0.03388 0.02611 0.0076 0.6244 0.7422
0.500 0.1228 0.03349 0.02564 0.0084 0.6187 0.7542
0.750 0.1512 0.03358 0.02578 0.0091 0.6110 0.7594
1.000 0.1672 0.03332 0.02549 0.0099 0.6042 0.7710
1.250 0.1986 0.03301 0.02508 0.0108 0.5991 0.7761
1.500 0.2107 0.03311 0.02528 0.0114 0.5901 0.7874
1.750 0.2414 0.03272 0.02485 0.0122 0.5840 0.7924
2.000 0.2602 0.03275 0.02491 0.0130 0.5763 0.8009
2.250 0.2830 0.03246 0.02462 0.0138 0.5690 0.8079
2.500 0.3098 0.03210 0.02416 0.0144 0.5636 0.8148
2.750 0.3236 0.03220 0.02437 0.0154 0.5543 0.8227
3.000 0.3533 0.03175 0.02384 0.0159 0.5484 0.8284
3.250 0.3655 0.03195 0.02413 0.0170 0.5397 0.8363
3.500 0.3932 0.03154 0.02369 0.0175 0.5328 0.8414
3.750 0.4150 0.03153 0.02369 0.0181 0.5251 0.8473
4.000 0.4316 0.03144 0.02361 0.0191 0.5171 0.8539
4.250 0.4635 0.03092 0.02299 0.0192 0.5114 0.8582
4.500 0.4790 0.03119 0.02341 0.0203 0.5010 0.8637
4.750 0.5054 0.03075 0.02284 0.0205 0.4954 0.8690
5.000 0.5211 0.03103 0.02328 0.0216 0.4851 0.8733
5.250 0.5517 0.03053 0.02268 0.0216 0.4787 0.8776
5.500 0.5665 0.03087 0.02314 0.0226 0.4686 0.8822
5.750 0.5941 0.03047 0.02266 0.0226 0.4619 0.8864
6.000 0.6122 0.03069 0.02300 0.0235 0.4521 0.8900
6.250 0.6419 0.03027 0.02251 0.0235 0.4449 0.8937
6.500 0.6591 0.03059 0.02295 0.0242 0.4354 0.8977
6.750 0.6877 0.03026 0.02254 0.0240 0.4280 0.9011
7.000 0.7061 0.03052 0.02292 0.0247 0.4186 0.9045
7.250 0.7363 0.03010 0.02244 0.0246 0.4109 0.9076
7.500 0.7545 0.03046 0.02292 0.0251 0.4015 0.9110
7.750 0.7853 0.03006 0.02245 0.0248 0.3938 0.9142
8.000 0.8032 0.03053 0.02304 0.0251 0.3843 0.9172
8.250 0.8352 0.03012 0.02255 0.0246 0.3768 0.9197
8.500 0.8517 0.03063 0.02321 0.0253 0.3673 0.9231
8.750 0.8853 0.03019 0.02265 0.0246 0.3598 0.9258
9.000 0.9009 0.03088 0.02352 0.0251 0.3502 0.9287
9.250 0.9365 0.03047 0.02294 0.0242 0.3428 0.9316
9.500 0.9491 0.03136 0.02405 0.0248 0.3333 0.9351
9.750 0.9867 0.03097 0.02346 0.0238 0.3260 0.9378
10.000 0.9962 0.03211 0.02488 0.0245 0.3169 0.9413
10.250 1.0352 0.03186 0.02440 0.0232 0.3095 0.9441
10.500 1.0415 0.03321 0.02606 0.0241 0.3008 0.9485
10.750 1.0807 0.03302 0.02566 0.0228 0.2933 0.9521
11.000 1.0852 0.03458 0.02754 0.0236 0.2854 0.9580
11.250 1.1220 0.03463 0.02745 0.0223 0.2778 0.9623
11.500 1.1297 0.03630 0.02940 0.0224 0.2706 0.9689
11.750 1.1589 0.03688 0.02996 0.0212 0.2632 0.9759
12.000 1.1769 0.03826 0.03145 0.0204 0.2565 0.9914
12.250 1.1797 0.03992 0.03330 0.0209 0.2503 1.0000
12.500 1.2278 0.04005 0.03321 0.0185 0.2432 1.0000
12.750 1.2061 0.04312 0.03667 0.0198 0.2385 1.0000
13.000 1.2151 0.04493 0.03858 0.0191 0.2327 1.0000
13.250 1.2544 0.04531 0.03882 0.0178 0.2265 1.0000
13.500 1.2171 0.05036 0.04427 0.0174 0.2228 1.0000
13.750 1.1863 0.05591 0.05009 0.0156 0.2187 1.0000
14.000 1.2752 0.05180 0.04561 0.0157 0.2113 1.0000
14.250 1.1910 0.06203 0.05634 0.0130 0.2097 1.0000
14.500 0.6875 0.15183 0.14662 -0.0268 0.2117 1.0000
15.000 1.1867 0.07272 0.06724 0.0085 0.1965 1.0000
15.250 0.6512 0.17386 0.16879 -0.0423 0.2305 1.0000
15.500 0.7043 0.17958 0.17457 -0.0415 0.2280 1.0000
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