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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.3518 0.09217 0.08783 0.0012 1.0000 0.0203 -19.500 -1.3619 0.08740 0.08299 -0.0005 1.0000 0.0209 -19.250 -1.3698 0.08297 0.07848 -0.0020 1.0000 0.0215 -19.000 -1.3757 0.07889 0.07432 -0.0033 1.0000 0.0221 -18.750 -1.3794 0.07516 0.07050 -0.0044 1.0000 0.0227 -18.500 -1.3862 0.07106 0.06634 -0.0055 1.0000 0.0234 -18.250 -1.3914 0.06723 0.06244 -0.0065 1.0000 0.0243 -18.000 -1.3939 0.06379 0.05895 -0.0073 1.0000 0.0252 -17.750 -1.3942 0.06068 0.05577 -0.0079 1.0000 0.0261 -17.500 -1.3918 0.05790 0.05293 -0.0084 1.0000 0.0269 -17.250 -1.3933 0.05474 0.04972 -0.0089 1.0000 0.0280 -17.000 -1.3923 0.05193 0.04686 -0.0093 1.0000 0.0292 -16.750 -1.3888 0.04944 0.04433 -0.0095 1.0000 0.0304 -16.500 -1.3836 0.04717 0.04200 -0.0097 1.0000 0.0315 -16.250 -1.3812 0.04468 0.03948 -0.0098 1.0000 0.0332 -16.000 -1.3762 0.04252 0.03730 -0.0097 1.0000 0.0349 -15.750 -1.3689 0.04059 0.03533 -0.0096 1.0000 0.0365 -15.500 -1.3633 0.03859 0.03330 -0.0094 1.0000 0.0385 -15.250 -1.3567 0.03673 0.03142 -0.0092 1.0000 0.0407 -15.000 -1.3470 0.03518 0.02985 -0.0089 1.0000 0.0426 -14.750 -1.3407 0.03343 0.02810 -0.0084 1.0000 0.0452 -14.500 -1.3322 0.03190 0.02656 -0.0080 1.0000 0.0478 -14.250 -1.3212 0.03058 0.02520 -0.0075 1.0000 0.0501 -14.000 -1.3127 0.02907 0.02371 -0.0070 1.0000 0.0534 -13.750 -1.3014 0.02779 0.02242 -0.0065 1.0000 0.0563 -13.500 -1.2893 0.02657 0.02119 -0.0060 1.0000 0.0597 -13.250 -1.2782 0.02528 0.01992 -0.0055 1.0000 0.0635 -13.000 -1.2636 0.02425 0.01888 -0.0051 1.0000 0.0670 -12.750 -1.2516 0.02303 0.01769 -0.0046 1.0000 0.0717 -12.500 -1.2360 0.02207 0.01674 -0.0043 1.0000 0.0760 -12.250 -1.2223 0.02095 0.01565 -0.0039 1.0000 0.0816 -12.000 -1.2057 0.02004 0.01476 -0.0036 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0.00459 -0.0057 0.6728 0.2494 -6.750 -0.7037 0.00992 0.00434 -0.0060 0.6630 0.2628 -6.250 -0.6466 0.00942 0.00388 -0.0068 0.6414 0.2913 -6.000 -0.6178 0.00919 0.00367 -0.0072 0.6305 0.3074 -5.750 -0.5889 0.00898 0.00347 -0.0076 0.6186 0.3233 -5.500 -0.5597 0.00877 0.00329 -0.0080 0.6065 0.3391 -5.250 -0.5306 0.00858 0.00311 -0.0084 0.5941 0.3565 -4.750 -0.4717 0.00825 0.00281 -0.0093 0.5710 0.3895 -4.500 -0.4422 0.00811 0.00268 -0.0097 0.5608 0.4063 -4.250 -0.4125 0.00798 0.00256 -0.0102 0.5512 0.4226 -4.000 -0.3827 0.00786 0.00245 -0.0106 0.5430 0.4386 -3.500 -0.3229 0.00766 0.00226 -0.0115 0.5280 0.4691 -3.250 -0.2928 0.00754 0.00217 -0.0120 0.5218 0.4845 -3.000 -0.2629 0.00745 0.00210 -0.0125 0.5154 0.4989 -2.750 -0.2329 0.00736 0.00203 -0.0129 0.5097 0.5153 -2.500 -0.2027 0.00725 0.00197 -0.0134 0.5046 0.5333 -2.250 -0.1726 0.00718 0.00194 -0.0138 0.4996 0.5529 -2.000 -0.1426 0.00718 0.00196 -0.0142 0.4941 0.5713 -1.750 -0.1120 0.00717 0.00198 -0.0147 0.4899 0.5869 -1.500 -0.0815 0.00721 0.00203 -0.0151 0.4852 0.5994 -1.250 -0.0511 0.00727 0.00208 -0.0155 0.4806 0.6076 -1.000 -0.0206 0.00736 0.00213 -0.0159 0.4760 0.6148 -0.750 0.0101 0.00739 0.00216 -0.0163 0.4723 0.6208 -0.500 0.0406 0.00747 0.00224 -0.0167 0.4679 0.6263 -0.250 0.0710 0.00757 0.00229 -0.0171 0.4630 0.6312 0.000 0.1015 0.00767 0.00234 -0.0175 0.4586 0.6350 0.250 0.1320 0.00770 0.00240 -0.0179 0.4553 0.6391 0.500 0.1624 0.00778 0.00249 -0.0183 0.4511 0.6426 0.750 0.1927 0.00788 0.00256 -0.0187 0.4465 0.6460 1.000 0.2230 0.00800 0.00264 -0.0191 0.4418 0.6494 1.250 0.2537 0.00807 0.00270 -0.0195 0.4382 0.6521 1.500 0.2839 0.00809 0.00273 -0.0199 0.4335 0.6551 1.750 0.3139 0.00818 0.00281 -0.0202 0.4289 0.6576 2.000 0.3440 0.00828 0.00291 -0.0205 0.4241 0.6601 2.250 0.3744 0.00833 0.00297 -0.0209 0.4192 0.6624 2.500 0.4046 0.00841 0.00303 -0.0213 0.4133 0.6647 2.750 0.4347 0.00853 0.00311 -0.0217 0.4076 0.6668 3.000 0.4651 0.00859 0.00318 -0.0221 0.4028 0.6684 3.250 0.4951 0.00862 0.00318 -0.0225 0.3963 0.6704 3.500 0.5248 0.00868 0.00324 -0.0228 0.3898 0.6722 3.750 0.5548 0.00874 0.00331 -0.0232 0.3829 0.6740 4.000 0.5842 0.00886 0.00341 -0.0235 0.3747 0.6756 4.250 0.6141 0.00894 0.00349 -0.0238 0.3666 0.6772 4.500 0.6435 0.00907 0.00358 -0.0241 0.3576 0.6788 4.750 0.6732 0.00918 0.00368 -0.0245 0.3489 0.6804 5.000 0.7024 0.00933 0.00379 -0.0248 0.3391 0.6819 5.250 0.7315 0.00950 0.00392 -0.0251 0.3281 0.6833 5.500 0.7606 0.00967 0.00405 -0.0254 0.3178 0.6846 5.750 0.7893 0.00988 0.00421 -0.0256 0.3071 0.6856 6.000 0.8179 0.01002 0.00431 -0.0259 0.2967 0.6872 6.250 0.8465 0.01016 0.00444 -0.0261 0.2879 0.6888 6.500 0.8745 0.01037 0.00463 -0.0263 0.2783 0.6904 6.750 0.9029 0.01055 0.00482 -0.0264 0.2698 0.6922 7.000 0.9305 0.01082 0.00505 -0.0265 0.2598 0.6939 7.250 0.9588 0.01101 0.00523 -0.0267 0.2517 0.6954 7.500 0.9863 0.01127 0.00545 -0.0268 0.2428 0.6964 7.750 1.0143 0.01147 0.00564 -0.0270 0.2354 0.6975 8.000 1.0414 0.01175 0.00589 -0.0271 0.2274 0.6986 8.250 1.0692 0.01195 0.00609 -0.0272 0.2210 0.6996 8.500 1.0956 0.01227 0.00636 -0.0272 0.2124 0.7004 8.750 1.1232 0.01248 0.00658 -0.0274 0.2067 0.7011 9.000 1.1495 0.01279 0.00685 -0.0274 0.1999 0.7018 9.250 1.1761 0.01306 0.00712 -0.0274 0.1939 0.7024 9.500 1.2023 0.01335 0.00740 -0.0273 0.1874 0.7030 9.750 1.2274 0.01367 0.00770 -0.0272 0.1806 0.7044 10.000 1.2536 0.01390 0.00796 -0.0272 0.1755 0.7057 10.250 1.2778 0.01429 0.00833 -0.0269 0.1687 0.7069 10.500 1.3026 0.01461 0.00866 -0.0267 0.1635 0.7079 10.750 1.3268 0.01496 0.00901 -0.0265 0.1579 0.7089 11.000 1.3489 0.01545 0.00948 -0.0260 0.1511 0.7099 11.250 1.3730 0.01577 0.00983 -0.0257 0.1471 0.7109 11.500 1.3946 0.01623 0.01028 -0.0252 0.1419 0.7120 11.750 1.4148 0.01676 0.01080 -0.0245 0.1365 0.7130 12.000 1.4365 0.01715 0.01123 -0.0240 0.1329 0.7141 12.250 1.4538 0.01771 0.01178 -0.0229 0.1282 0.7152 12.500 1.4660 0.01842 0.01250 -0.0213 0.1231 0.7163 12.750 1.4841 0.01899 0.01311 -0.0206 0.1204 0.7173 13.000 1.4989 0.01980 0.01393 -0.0197 0.1164 0.7183 13.250 1.5098 0.02093 0.01506 -0.0188 0.1117 0.7192 13.500 1.5236 0.02196 0.01613 -0.0183 0.1084 0.7199 13.750 1.5363 0.02312 0.01733 -0.0180 0.1046 0.7217 14.000 1.5452 0.02470 0.01893 -0.0178 0.1005 0.7235 14.250 1.5540 0.02636 0.02063 -0.0176 0.0970 0.7251 14.500 1.5648 0.02788 0.02221 -0.0176 0.0946 0.7265 14.750 1.5721 0.02973 0.02410 -0.0175 0.0918 0.7278 15.000 1.5758 0.03195 0.02636 -0.0175 0.0887 0.7292 15.250 1.5778 0.03436 0.02881 -0.0175 0.0857 0.7306 15.500 1.5835 0.03642 0.03094 -0.0175 0.0836 0.7320 15.750 1.5849 0.03893 0.03350 -0.0176 0.0809 0.7333 16.000 1.5819 0.04190 0.03650 -0.0177 0.0780 0.7345 16.250 1.5770 0.04513 0.03977 -0.0180 0.0751 0.7357 16.500 1.5772 0.04783 0.04254 -0.0182 0.0733 0.7367 16.750 1.5744 0.05092 0.04570 -0.0186 0.0712 0.7385 17.000 1.5694 0.05436 0.04919 -0.0191 0.0691 0.7403 17.250 1.5616 0.05816 0.05305 -0.0198 0.0668 0.7420 17.500 1.5568 0.06168 0.05665 -0.0204 0.0648 0.7437 17.750 1.5540 0.06498 0.06002 -0.0211 0.0632 0.7454 18.000 1.5474 0.06878 0.06388 -0.0219 0.0612 0.7471 18.250 1.5388 0.07290 0.06806 -0.0229 0.0594 0.7488 18.500 1.5273 0.07742 0.07263 -0.0240 0.0572 0.7504 18.750 1.5222 0.08117 0.07645 -0.0250 0.0556 0.7521 19.000 1.5155 0.08520 0.08055 -0.0261 0.0540 0.7536 19.250 1.5058 0.08968 0.08510 -0.0275 0.0523 0.7559