XFOIL Version 6.96 Calculated polar for: EPPLER 332 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4092 0.09254 0.08929 -0.0184 1.0000 0.0337 -8.500 -0.4164 0.08799 0.08478 -0.0242 1.0000 0.0340 -8.250 -0.4221 0.08438 0.08117 -0.0263 1.0000 0.0341 -8.000 -0.4336 0.08136 0.07813 -0.0268 1.0000 0.0342 -7.750 -0.4393 0.07826 0.07495 -0.0269 1.0000 0.0343 -7.500 -0.4421 0.07531 0.07189 -0.0263 1.0000 0.0345 -7.250 -0.4455 0.07003 0.06661 -0.0258 1.0000 0.0348 -7.000 -0.4397 0.06574 0.06244 -0.0249 1.0000 0.0356 -6.750 -0.4347 0.06290 0.05964 -0.0236 1.0000 0.0362 -6.500 -0.4307 0.06022 0.05696 -0.0221 1.0000 0.0371 -6.250 -0.4279 0.05771 0.05444 -0.0202 1.0000 0.0380 -6.000 -0.4077 0.05413 0.05075 -0.0222 0.9852 0.0399 -5.750 -0.3676 0.05219 0.04808 -0.0257 0.9393 0.0447 -5.500 -0.3424 0.04492 0.04068 -0.0293 0.9052 0.0463 -5.250 -0.3022 0.02554 0.02138 -0.0285 0.8009 0.0489 -5.000 -0.2895 0.02321 0.01880 -0.0267 0.7808 0.0519 -4.500 -0.2631 0.01808 0.01295 -0.0227 0.7454 0.0596 -4.250 -0.2461 0.01619 0.01093 -0.0215 0.7292 0.0627 -4.000 -0.2296 0.01457 0.00876 -0.0190 0.7134 0.0719 -3.750 -0.2156 0.02999 0.02376 -0.0195 0.7268 0.0749 -3.250 -0.1599 0.02274 0.01513 -0.0139 0.6994 0.0314 -3.000 -0.1315 0.02119 0.01295 -0.0121 0.6854 0.0261 -2.750 -0.1041 0.01912 0.01064 -0.0114 0.6718 0.0253 -2.500 -0.0764 0.01787 0.00916 -0.0107 0.6584 0.0255 -2.250 -0.0496 0.01678 0.00793 -0.0099 0.6451 0.0267 -2.000 -0.0250 0.01605 0.00722 -0.0093 0.6324 0.0315 -1.750 -0.0004 0.01540 0.00646 -0.0082 0.6206 0.0348 -1.500 0.0212 0.01458 0.00560 -0.0066 0.6104 0.0415 -1.250 0.1406 0.01330 0.00725 -0.0199 0.5931 0.9598 -1.000 0.2789 0.01269 0.00611 -0.0417 0.5732 1.0000 -0.750 0.3017 0.01269 0.00592 -0.0410 0.5641 1.0000 -0.500 0.3248 0.01268 0.00578 -0.0403 0.5542 1.0000 -0.250 0.3480 0.01269 0.00566 -0.0396 0.5449 1.0000 0.000 0.3713 0.01272 0.00554 -0.0389 0.5368 1.0000 0.250 0.3949 0.01274 0.00549 -0.0383 0.5280 1.0000 0.500 0.4184 0.01282 0.00541 -0.0376 0.5209 1.0000 0.750 0.4421 0.01285 0.00540 -0.0370 0.5122 1.0000 1.000 0.4657 0.01295 0.00535 -0.0363 0.5055 1.0000 1.250 0.4895 0.01299 0.00540 -0.0357 0.4975 1.0000 1.500 0.5133 0.01311 0.00538 -0.0350 0.4910 1.0000 1.750 0.5372 0.01318 0.00546 -0.0344 0.4835 1.0000 2.000 0.5611 0.01329 0.00548 -0.0338 0.4773 1.0000 2.250 0.5849 0.01341 0.00559 -0.0332 0.4705 1.0000 2.500 0.6088 0.01351 0.00565 -0.0326 0.4641 1.0000 2.750 0.6328 0.01367 0.00576 -0.0320 0.4583 1.0000 3.000 0.6566 0.01379 0.00589 -0.0314 0.4517 1.0000 3.250 0.6806 0.01395 0.00596 -0.0307 0.4463 1.0000 3.500 0.7042 0.01409 0.00618 -0.0301 0.4398 1.0000 3.750 0.7281 0.01424 0.00630 -0.0295 0.4341 1.0000 4.000 0.7519 0.01443 0.00647 -0.0289 0.4286 1.0000 4.250 0.7753 0.01458 0.00667 -0.0282 0.4223 1.0000 4.500 0.7993 0.01476 0.00682 -0.0276 0.4171 1.0000 4.750 0.8225 0.01495 0.00709 -0.0269 0.4111 1.0000 5.000 0.8459 0.01512 0.00728 -0.0262 0.4052 1.0000 5.250 0.8696 0.01535 0.00748 -0.0256 0.4001 1.0000 5.500 0.8920 0.01552 0.00778 -0.0248 0.3936 1.0000 5.750 0.9154 0.01570 0.00794 -0.0240 0.3880 1.0000 6.000 0.9377 0.01595 0.00828 -0.0232 0.3821 1.0000 6.250 0.9601 0.01613 0.00852 -0.0223 0.3757 1.0000 6.500 0.9828 0.01637 0.00875 -0.0215 0.3701 1.0000 6.750 1.0040 0.01656 0.00908 -0.0205 0.3630 1.0000 7.000 1.0267 0.01677 0.00925 -0.0197 0.3573 1.0000 7.250 1.0469 0.01699 0.00965 -0.0185 0.3499 1.0000 7.500 1.0687 0.01717 0.00981 -0.0175 0.3435 1.0000 7.750 1.0884 0.01741 0.01021 -0.0162 0.3360 1.0000 8.000 1.1093 0.01758 0.01039 -0.0151 0.3291 1.0000 8.250 1.1280 0.01782 0.01078 -0.0136 0.3209 1.0000 8.500 1.1482 0.01800 0.01094 -0.0124 0.3136 1.0000 8.750 1.1654 0.01822 0.01135 -0.0107 0.3047 1.0000 9.000 1.1834 0.01844 0.01163 -0.0091 0.2964 1.0000 9.250 1.2000 0.01865 0.01194 -0.0073 0.2872 1.0000 9.500 1.2154 0.01891 0.01233 -0.0054 0.2773 1.0000 9.750 1.2303 0.01919 0.01266 -0.0033 0.2678 1.0000 10.000 1.2435 0.01948 0.01300 -0.0010 0.2573 1.0000 10.250 1.2550 0.01980 0.01347 0.0016 0.2456 1.0000 10.500 1.2650 0.02019 0.01394 0.0043 0.2334 1.0000 10.750 1.2731 0.02065 0.01446 0.0073 0.2210 1.0000 11.000 1.2790 0.02119 0.01505 0.0106 0.2081 1.0000 11.250 1.2826 0.02183 0.01571 0.0141 0.1948 1.0000 11.500 1.2835 0.02259 0.01649 0.0178 0.1816 1.0000 11.750 1.2799 0.02345 0.01735 0.0221 0.1699 1.0000 12.000 1.2754 0.02452 0.01842 0.0260 0.1588 1.0000 12.250 1.2702 0.02595 0.01983 0.0291 0.1478 1.0000 12.500 1.2652 0.02772 0.02162 0.0312 0.1372 1.0000 12.750 1.2609 0.02980 0.02377 0.0326 0.1269 1.0000 13.000 1.2554 0.03225 0.02628 0.0334 0.1179 1.0000 13.250 1.2464 0.03525 0.02924 0.0338 0.1105 1.0000 13.500 1.2413 0.03814 0.03223 0.0337 0.1023 1.0000 13.750 1.2329 0.04146 0.03559 0.0335 0.0956 1.0000 14.000 1.2249 0.04489 0.03904 0.0331 0.0896 1.0000 14.250 1.2166 0.04839 0.04259 0.0326 0.0841 1.0000 14.500 1.2080 0.05208 0.04634 0.0318 0.0786 1.0000 14.750 1.1987 0.05579 0.05005 0.0312 0.0741 1.0000 15.000 1.1911 0.05960 0.05398 0.0301 0.0690 1.0000 15.250 1.1824 0.06341 0.05772 0.0293 0.0650 1.0000 15.500 1.1760 0.06736 0.06183 0.0280 0.0607 1.0000 15.750 1.1689 0.07144 0.06596 0.0266 0.0570 1.0000 16.000 1.1634 0.07509 0.06959 0.0258 0.0533 1.0000 16.250 1.1574 0.07927 0.07391 0.0243 0.0499 1.0000 16.500 1.1517 0.08335 0.07803 0.0228 0.0470 1.0000 16.750 1.1482 0.08689 0.08157 0.0219 0.0437 1.0000 17.000 1.1428 0.09122 0.08605 0.0202 0.0413 1.0000 17.250 1.1382 0.09542 0.09035 0.0184 0.0390 1.0000 17.500 1.1396 0.09799 0.09280 0.0182 0.0360 1.0000 17.750 1.1334 0.10276 0.09778 0.0161 0.0347 1.0000 18.000 1.1279 0.10733 0.10251 0.0142 0.0330 1.0000 18.250 1.1236 0.11172 0.10699 0.0121 0.0314 1.0000 18.500 1.1228 0.11533 0.11059 0.0106 0.0297 1.0000 18.750 1.1195 0.11921 0.11454 0.0094 0.0281 1.0000 19.000 1.1114 0.12468 0.12019 0.0064 0.0274 1.0000 19.250 1.1017 0.13050 0.12619 0.0034 0.0266 1.0000