XFOIL Version 6.96 Calculated polar for: EPPLER 1098 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.5284 0.11054 0.10727 -0.0940 0.7793 0.0047 -18.250 -0.5564 0.10097 0.09754 -0.0990 0.7743 0.0047 -18.000 -0.5712 0.09410 0.09055 -0.1028 0.7670 0.0047 -17.750 -0.6041 0.08453 0.08078 -0.1080 0.7621 0.0047 -17.500 -0.6127 0.07936 0.07549 -0.1109 0.7551 0.0047 -17.250 -0.6233 0.07408 0.07006 -0.1137 0.7480 0.0047 -17.000 -0.6412 0.06807 0.06388 -0.1168 0.7424 0.0047 -16.750 -0.6416 0.06466 0.06037 -0.1186 0.7358 0.0047 -16.500 -0.6449 0.06105 0.05664 -0.1203 0.7293 0.0047 -16.250 -0.6561 0.05664 0.05208 -0.1221 0.7244 0.0047 -16.000 -0.6654 0.05275 0.04804 -0.1235 0.7187 0.0048 -15.500 -0.6694 0.04699 0.04206 -0.1251 0.7088 0.0048 -15.250 -0.6717 0.04429 0.03924 -0.1257 0.7040 0.0049 -15.000 -0.6729 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0.6043 0.5279 -0.500 0.4606 0.00759 0.00205 -0.1176 0.6035 0.5292 -0.250 0.4899 0.00759 0.00206 -0.1181 0.6026 0.5307 0.000 0.5193 0.00760 0.00208 -0.1186 0.6016 0.5321 0.250 0.5486 0.00762 0.00210 -0.1191 0.6006 0.5333 0.500 0.5779 0.00764 0.00212 -0.1196 0.5997 0.5346 0.750 0.6072 0.00766 0.00215 -0.1201 0.5988 0.5359 1.000 0.6364 0.00769 0.00218 -0.1206 0.5979 0.5372 1.250 0.6656 0.00772 0.00222 -0.1211 0.5967 0.5386 1.500 0.6946 0.00776 0.00225 -0.1215 0.5954 0.5401 1.750 0.7234 0.00781 0.00229 -0.1220 0.5937 0.5416 2.000 0.7523 0.00786 0.00234 -0.1224 0.5918 0.5428 2.250 0.7811 0.00787 0.00237 -0.1228 0.5899 0.5439 2.500 0.8097 0.00786 0.00241 -0.1232 0.5875 0.5454 2.750 0.8382 0.00786 0.00244 -0.1235 0.5844 0.5469 3.000 0.8663 0.00788 0.00246 -0.1238 0.5809 0.5484 3.250 0.8940 0.00794 0.00251 -0.1240 0.5774 0.5500 3.500 0.9226 0.00794 0.00257 -0.1243 0.5748 0.5516 3.750 0.9511 0.00796 0.00263 -0.1247 0.5719 0.5532 4.000 0.9793 0.00800 0.00270 -0.1250 0.5690 0.5549 4.250 1.0071 0.00804 0.00276 -0.1252 0.5659 0.5567 4.500 1.0344 0.00811 0.00283 -0.1254 0.5629 0.5584 4.750 1.0627 0.00814 0.00292 -0.1257 0.5596 0.5601 5.000 1.0904 0.00818 0.00301 -0.1260 0.5554 0.5622 5.250 1.1171 0.00823 0.00309 -0.1260 0.5503 0.5643 5.500 1.1442 0.00829 0.00319 -0.1261 0.5446 0.5664 5.750 1.1694 0.00838 0.00329 -0.1259 0.5347 0.5685 6.000 1.1925 0.00853 0.00341 -0.1252 0.5156 0.5707 6.250 1.2065 0.00898 0.00368 -0.1228 0.4775 0.5727 6.500 1.2167 0.00958 0.00411 -0.1199 0.4407 0.5746 6.750 1.2258 0.01015 0.00455 -0.1167 0.4107 0.5767 7.000 1.2303 0.01069 0.00499 -0.1126 0.3848 0.5791 7.250 1.2364 0.01127 0.00549 -0.1089 0.3614 0.5816 7.500 1.2409 0.01194 0.00608 -0.1051 0.3383 0.5843 7.750 1.2375 0.01290 0.00689 -0.1002 0.3074 0.5869 8.000 1.2402 0.01374 0.00766 -0.0966 0.2874 0.5896 8.250 1.2428 0.01468 0.00854 -0.0932 0.2698 0.5927 8.500 1.2446 0.01576 0.00958 -0.0899 0.2518 0.5958 8.750 1.2486 0.01686 0.01065 -0.0872 0.2369 0.5992 9.000 1.2524 0.01807 0.01183 -0.0847 0.2222 0.6027 9.250 1.2545 0.01947 0.01318 -0.0822 0.2051 0.6058 9.500 1.2543 0.02109 0.01473 -0.0796 0.1856 0.6091 9.750 1.2546 0.02275 0.01632 -0.0772 0.1679 0.6130 10.000 1.2541 0.02453 0.01802 -0.0748 0.1471 0.6170 10.250 1.2534 0.02636 0.01975 -0.0726 0.1282 0.6208 10.500 1.2563 0.02801 0.02136 -0.0707 0.1132 0.6249 10.750 1.2606 0.02959 0.02291 -0.0691 0.1001 0.6296 11.000 1.2657 0.03118 0.02446 -0.0677 0.0885 0.6347 11.500 1.2769 0.03440 0.02762 -0.0650 0.0661 0.6457 11.750 1.2826 0.03606 0.02926 -0.0639 0.0558 0.6521 12.000 1.2892 0.03770 0.03088 -0.0628 0.0462 0.6583 12.250 1.2944 0.03950 0.03267 -0.0617 0.0368 0.6664 12.500 1.3011 0.04121 0.03437 -0.0608 0.0294 0.6738 12.750 1.3090 0.04285 0.03603 -0.0600 0.0242 0.6829 13.000 1.3140 0.04479 0.03797 -0.0591 0.0174 0.6919 13.250 1.3220 0.04650 0.03971 -0.0585 0.0135 0.7019 13.500 1.3270 0.04852 0.04175 -0.0577 0.0086 0.7131 13.750 1.3339 0.05039 0.04368 -0.0571 0.0058 0.7258 14.000 1.3427 0.05212 0.04549 -0.0567 0.0050 0.7411 14.250 1.3508 0.05394 0.04740 -0.0562 0.0042 0.7594 14.500 1.3598 0.05567 0.04924 -0.0558 0.0038 0.7834 14.750 1.3678 0.05748 0.05120 -0.0554 0.0035 0.8204 15.250 1.3839 0.06095 0.05508 -0.0547 0.0031 1.0000 15.500 1.3917 0.06301 0.05718 -0.0545 0.0030 1.0000 15.750 1.3992 0.06510 0.05933 -0.0544 0.0029 1.0000 16.000 1.4056 0.06737 0.06164 -0.0543 0.0027 1.0000 16.250 1.4111 0.06976 0.06409 -0.0543 0.0026 1.0000 16.500 1.4170 0.07213 0.06653 -0.0543 0.0025 1.0000 16.750 1.4212 0.07477 0.06923 -0.0544 0.0024 1.0000 17.000 1.4250 0.07749 0.07202 -0.0546 0.0023 1.0000 17.250 1.4294 0.08019 0.07479 -0.0549 0.0023 1.0000 17.500 1.4341 0.08287 0.07754 -0.0552 0.0023 1.0000 17.750 1.4368 0.08588 0.08062 -0.0556 0.0022 1.0000 18.000 1.4393 0.08892 0.08373 -0.0561 0.0022 1.0000 18.250 1.4418 0.09202 0.08691 -0.0567 0.0022 1.0000 18.500 1.4431 0.09533 0.09030 -0.0574 0.0021 1.0000 18.750 1.4441 0.09872 0.09377 -0.0582 0.0021 1.0000 19.000 1.4447 0.10223 0.09737 -0.0591 0.0021 1.0000 19.250 1.4437 0.10599 0.10122 -0.0602 0.0020 1.0000