XFOIL Version 6.96 Calculated polar for: NREL's S803 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.000 -0.8342 0.04188 0.03951 -0.0851 0.9984 0.0067 -12.750 -0.8375 0.03538 0.03277 -0.0945 0.9952 0.0068 -12.500 -0.8356 0.03092 0.02810 -0.1006 0.9904 0.0069 -12.250 -0.8129 0.02862 0.02565 -0.1049 0.9875 0.0070 -12.000 -0.7844 0.02776 0.02474 -0.1071 0.9861 0.0072 -11.750 -0.7569 0.02633 0.02320 -0.1099 0.9848 0.0073 -11.500 -0.7301 0.02598 0.02285 -0.1107 0.9829 0.0075 -11.250 -0.7123 0.02457 0.02131 -0.1111 0.9784 0.0076 -11.000 -0.6865 0.02329 0.01990 -0.1128 0.9756 0.0078 -10.750 -0.6585 0.02203 0.01851 -0.1146 0.9736 0.0080 -10.500 -0.6400 0.02094 0.01728 -0.1142 0.9680 0.0082 -10.250 -0.6154 0.01974 0.01593 -0.1150 0.9634 0.0084 -10.000 -0.5894 0.01864 0.01468 -0.1159 0.9593 0.0086 -9.750 -0.5670 0.01780 0.01372 -0.1156 0.9518 0.0088 -9.250 -0.5068 0.01618 0.01185 -0.1181 0.9414 0.0091 -9.000 -0.4721 0.01501 0.01054 -0.1206 0.9368 0.0094 -8.750 -0.4320 0.01435 0.00981 -0.1238 0.9327 0.0098 -8.500 -0.3883 0.01383 0.00923 -0.1277 0.9263 0.0101 -8.250 -0.3438 0.01332 0.00863 -0.1318 0.9167 0.0104 -8.000 -0.3055 0.01279 0.00796 -0.1345 0.8999 0.0107 -7.750 -0.2746 0.01233 0.00736 -0.1355 0.8801 0.0111 -7.500 -0.2473 0.01196 0.00683 -0.1357 0.8610 0.0113 -7.250 -0.2214 0.01162 0.00635 -0.1355 0.8434 0.0116 -7.000 -0.1956 0.01132 0.00593 -0.1353 0.8270 0.0119 -6.750 -0.1698 0.01107 0.00556 -0.1351 0.8113 0.0121 -6.500 -0.1438 0.01082 0.00521 -0.1348 0.7965 0.0123 -6.250 -0.1182 0.01034 0.00462 -0.1347 0.7827 0.0129 -6.000 -0.0916 0.01008 0.00429 -0.1347 0.7700 0.0133 -5.750 -0.0647 0.00985 0.00399 -0.1346 0.7588 0.0137 -5.500 -0.0376 0.00963 0.00370 -0.1346 0.7484 0.0141 -5.000 0.0171 0.00923 0.00316 -0.1346 0.7281 0.0149 -4.750 0.0445 0.00907 0.00293 -0.1346 0.7187 0.0153 -4.500 0.0721 0.00892 0.00272 -0.1346 0.7091 0.0157 -4.250 0.1001 0.00878 0.00252 -0.1347 0.7010 0.0162 -4.000 0.1279 0.00859 0.00229 -0.1348 0.6930 0.0173 -3.750 0.1561 0.00845 0.00212 -0.1349 0.6859 0.0182 -3.500 0.1842 0.00835 0.00197 -0.1350 0.6786 0.0191 -3.250 0.2124 0.00826 0.00184 -0.1351 0.6718 0.0201 -3.000 0.2406 0.00817 0.00172 -0.1352 0.6646 0.0224 -2.750 0.2688 0.00805 0.00161 -0.1354 0.6583 0.0307 -2.500 0.2975 0.00786 0.00151 -0.1357 0.6522 0.0584 -2.250 0.3259 0.00769 0.00143 -0.1359 0.6466 0.0933 -2.000 0.3547 0.00753 0.00137 -0.1363 0.6415 0.1318 -1.750 0.3834 0.00737 0.00132 -0.1366 0.6359 0.1755 -1.250 0.4412 0.00701 0.00124 -0.1374 0.6257 0.2909 -1.000 0.4707 0.00668 0.00121 -0.1382 0.6210 0.4027 -0.750 0.5001 0.00632 0.00123 -0.1388 0.6164 0.5474 -0.500 0.5287 0.00629 0.00129 -0.1390 0.6121 0.5910 -0.250 0.5572 0.00632 0.00132 -0.1391 0.6074 0.6065 0.000 0.5853 0.00636 0.00136 -0.1391 0.6027 0.6201 0.250 0.6134 0.00642 0.00139 -0.1391 0.5976 0.6298 0.500 0.6416 0.00646 0.00144 -0.1392 0.5911 0.6373 0.750 0.6692 0.00655 0.00148 -0.1391 0.5838 0.6451 1.000 0.6972 0.00659 0.00153 -0.1391 0.5760 0.6520 1.250 0.7247 0.00668 0.00159 -0.1390 0.5680 0.6588 1.500 0.7525 0.00674 0.00165 -0.1389 0.5594 0.6660 1.750 0.7799 0.00683 0.00172 -0.1388 0.5502 0.6737 2.000 0.8072 0.00693 0.00178 -0.1387 0.5399 0.6791 2.250 0.8347 0.00700 0.00186 -0.1386 0.5301 0.6831 2.500 0.8619 0.00711 0.00194 -0.1385 0.5189 0.6862 2.750 0.8887 0.00723 0.00202 -0.1383 0.5041 0.6891 3.000 0.9152 0.00738 0.00211 -0.1380 0.4870 0.6917 3.250 0.9409 0.00759 0.00223 -0.1376 0.4631 0.6945 3.500 0.9649 0.00793 0.00241 -0.1370 0.4224 0.6974 3.750 0.9873 0.00841 0.00267 -0.1360 0.3747 0.7003 4.000 1.0095 0.00893 0.00297 -0.1351 0.3275 0.7034 4.250 1.0314 0.00946 0.00329 -0.1341 0.2811 0.7063 4.500 1.0537 0.00994 0.00359 -0.1332 0.2423 0.7094 4.750 1.0771 0.01033 0.00387 -0.1325 0.2148 0.7129 5.000 1.0998 0.01075 0.00416 -0.1317 0.1863 0.7167 5.250 1.1226 0.01116 0.00447 -0.1309 0.1616 0.7203 5.500 1.1454 0.01156 0.00477 -0.1301 0.1410 0.7238 5.750 1.1681 0.01194 0.00508 -0.1292 0.1226 0.7276 6.000 1.1910 0.01230 0.00538 -0.1284 0.1079 0.7318 6.250 1.2137 0.01267 0.00570 -0.1276 0.0949 0.7363 6.500 1.2362 0.01303 0.00603 -0.1267 0.0842 0.7409 6.750 1.2590 0.01335 0.00635 -0.1259 0.0763 0.7463 7.000 1.2816 0.01368 0.00667 -0.1251 0.0695 0.7519 7.250 1.3031 0.01407 0.00704 -0.1240 0.0618 0.7572 7.500 1.3253 0.01439 0.00738 -0.1231 0.0568 0.7635 7.750 1.3461 0.01478 0.00777 -0.1220 0.0516 0.7699 8.000 1.3676 0.01511 0.00813 -0.1210 0.0482 0.7770 8.500 1.4069 0.01589 0.00896 -0.1183 0.0404 0.7941 8.750 1.4255 0.01623 0.00935 -0.1167 0.0384 0.8045 9.000 1.4423 0.01664 0.00980 -0.1149 0.0358 0.8167 9.250 1.4581 0.01710 0.01031 -0.1129 0.0329 0.8310 9.500 1.4752 0.01747 0.01076 -0.1111 0.0316 0.8483 9.750 1.4906 0.01789 0.01126 -0.1091 0.0297 0.8725 10.000 1.4999 0.01821 0.01173 -0.1058 0.0275 1.0000 10.250 1.5149 0.01878 0.01232 -0.1039 0.0254 1.0000 10.500 1.5305 0.01934 0.01291 -0.1022 0.0239 1.0000 10.750 1.5446 0.01997 0.01357 -0.1003 0.0224 1.0000 11.000 1.5579 0.02069 0.01430 -0.0983 0.0210 1.0000 11.250 1.5715 0.02139 0.01505 -0.0964 0.0200 1.0000 11.500 1.5850 0.02211 0.01582 -0.0946 0.0192 1.0000 11.750 1.5975 0.02291 0.01666 -0.0928 0.0183 1.0000 12.000 1.6089 0.02381 0.01759 -0.0909 0.0171 1.0000 12.250 1.6193 0.02482 0.01864 -0.0890 0.0160 1.0000 12.500 1.6307 0.02578 0.01966 -0.0873 0.0153 1.0000 12.750 1.6414 0.02683 0.02077 -0.0857 0.0144 1.0000 13.000 1.6509 0.02802 0.02199 -0.0840 0.0134 1.0000 13.250 1.6593 0.02933 0.02334 -0.0824 0.0125 1.0000 13.500 1.6684 0.03064 0.02471 -0.0809 0.0118 1.0000 13.750 1.6769 0.03204 0.02618 -0.0796 0.0111 1.0000 14.000 1.6842 0.03360 0.02779 -0.0782 0.0102 1.0000 14.250 1.6901 0.03534 0.02959 -0.0769 0.0094 1.0000 14.500 1.6971 0.03704 0.03136 -0.0758 0.0089 1.0000 14.750 1.7028 0.03891 0.03329 -0.0748 0.0082 1.0000 15.000 1.7074 0.04095 0.03540 -0.0738 0.0075 1.0000 15.250 1.7110 0.04316 0.03768 -0.0729 0.0069 1.0000 15.500 1.7152 0.04537 0.03997 -0.0722 0.0065 1.0000 15.750 1.7181 0.04781 0.04248 -0.0716 0.0059 1.0000 16.000 1.7197 0.05044 0.04519 -0.0711 0.0055 1.0000 16.250 1.7203 0.05328 0.04812 -0.0707 0.0050 1.0000 16.500 1.7219 0.05609 0.05103 -0.0705 0.0048 1.0000 16.750 1.7224 0.05912 0.05415 -0.0705 0.0045 1.0000 17.000 1.7219 0.06237 0.05750 -0.0706 0.0043 1.0000 17.250 1.7203 0.06584 0.06106 -0.0709 0.0041 1.0000 17.500 1.7175 0.06958 0.06490 -0.0713 0.0039 1.0000 17.750 1.7137 0.07359 0.06902 -0.0720 0.0037 1.0000 18.000 1.7087 0.07789 0.07342 -0.0729 0.0035 1.0000 18.250 1.7028 0.08243 0.07807 -0.0741 0.0034 1.0000 18.500 1.6974 0.08701 0.08278 -0.0754 0.0034 1.0000 18.750 1.6906 0.09195 0.08784 -0.0770 0.0033 1.0000 19.000 1.6829 0.09716 0.09318 -0.0789 0.0032 1.0000 19.250 1.6738 0.10274 0.09888 -0.0811 0.0032 1.0000