XFOIL Version 6.96 Calculated polar for: NREL's S805A Airfoil 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.3275 0.10206 0.09990 -0.0461 1.0000 0.0217 -11.500 -0.3329 0.09676 0.09462 -0.0482 1.0000 0.0218 -8.750 -0.5712 0.04721 0.04419 -0.0603 0.9861 0.0226 -8.500 -0.5482 0.04475 0.04169 -0.0628 0.9810 0.0232 -8.250 -0.5265 0.04207 0.03889 -0.0649 0.9741 0.0240 -8.000 -0.5076 0.03906 0.03567 -0.0660 0.9639 0.0253 -7.000 -0.4450 0.02333 0.01773 -0.0605 0.8609 0.0221 -6.750 -0.4241 0.02175 0.01580 -0.0592 0.8336 0.0220 -6.500 -0.4010 0.02060 0.01441 -0.0583 0.8125 0.0217 -6.000 -0.3537 0.01773 0.01105 -0.0568 0.7818 0.0217 -5.750 -0.3290 0.01639 0.00955 -0.0562 0.7696 0.0219 -5.500 -0.3059 0.01488 0.00794 -0.0555 0.7589 0.0226 -5.250 -0.2835 0.01409 0.00708 -0.0547 0.7495 0.0236 -5.000 -0.2604 0.01352 0.00644 -0.0539 0.7404 0.0243 -4.750 -0.2374 0.01300 0.00584 -0.0532 0.7329 0.0251 -4.500 -0.2140 0.01254 0.00531 -0.0525 0.7256 0.0260 -4.250 -0.1903 0.01216 0.00484 -0.0518 0.7195 0.0270 -4.000 -0.1658 0.01181 0.00443 -0.0513 0.7130 0.0281 -3.750 -0.1420 0.01140 0.00392 -0.0507 0.7074 0.0301 -3.500 -0.1169 0.01110 0.00362 -0.0503 0.7019 0.0342 -3.250 -0.0916 0.01079 0.00330 -0.0499 0.6966 0.0427 -3.000 -0.0717 0.00989 0.00291 -0.0490 0.6922 0.1724 -2.750 -0.0564 0.00848 0.00250 -0.0478 0.6878 0.4399 -2.500 -0.0384 0.00756 0.00241 -0.0463 0.6834 0.6554 -2.250 -0.0124 0.00757 0.00250 -0.0458 0.6793 0.7115 -2.000 0.0150 0.00768 0.00256 -0.0456 0.6754 0.7382 -1.750 0.0422 0.00777 0.00267 -0.0453 0.6714 0.7566 -1.500 0.0687 0.00797 0.00288 -0.0447 0.6676 0.7773 -1.250 0.0944 0.00829 0.00319 -0.0438 0.6642 0.7984 -1.000 0.1207 0.00855 0.00343 -0.0430 0.6610 0.8090 -0.750 0.1487 0.00858 0.00344 -0.0431 0.6575 0.8144 -0.500 0.1766 0.00860 0.00344 -0.0431 0.6539 0.8172 -0.250 0.2049 0.00864 0.00345 -0.0433 0.6508 0.8204 0.000 0.2334 0.00870 0.00344 -0.0436 0.6479 0.8239 0.250 0.2624 0.00876 0.00344 -0.0440 0.6449 0.8275 0.500 0.2902 0.00876 0.00346 -0.0441 0.6416 0.8301 0.750 0.3182 0.00880 0.00350 -0.0442 0.6385 0.8328 1.000 0.3463 0.00885 0.00353 -0.0443 0.6356 0.8359 1.250 0.3749 0.00892 0.00357 -0.0446 0.6327 0.8396 1.500 0.4038 0.00900 0.00361 -0.0451 0.6299 0.8430 1.750 0.4312 0.00900 0.00366 -0.0451 0.6266 0.8454 2.000 0.4590 0.00903 0.00371 -0.0452 0.6230 0.8479 2.250 0.4871 0.00907 0.00374 -0.0453 0.6194 0.8507 2.500 0.5155 0.00915 0.00380 -0.0456 0.6156 0.8536 2.750 0.5435 0.00915 0.00384 -0.0458 0.6108 0.8569 3.000 0.5708 0.00914 0.00384 -0.0458 0.6056 0.8594 3.250 0.5980 0.00918 0.00388 -0.0458 0.6003 0.8618 3.500 0.6247 0.00915 0.00391 -0.0456 0.5939 0.8647 3.750 0.6521 0.00917 0.00393 -0.0457 0.5881 0.8679 4.000 0.6795 0.00918 0.00398 -0.0458 0.5817 0.8713 4.250 0.7062 0.00916 0.00399 -0.0456 0.5752 0.8740 4.500 0.7324 0.00918 0.00406 -0.0454 0.5684 0.8766 4.750 0.7587 0.00917 0.00411 -0.0452 0.5610 0.8798 5.000 0.7854 0.00921 0.00418 -0.0451 0.5544 0.8833 5.250 0.8120 0.00922 0.00422 -0.0450 0.5447 0.8869 5.500 0.8365 0.00919 0.00427 -0.0444 0.5320 0.8899 5.750 0.8609 0.00921 0.00433 -0.0438 0.5174 0.8933 6.000 0.8854 0.00928 0.00441 -0.0433 0.5005 0.8971 6.250 0.9097 0.00939 0.00451 -0.0428 0.4759 0.9012 6.500 0.9281 0.00964 0.00466 -0.0411 0.4326 0.9052 6.750 0.9411 0.01027 0.00500 -0.0386 0.3687 0.9105 7.000 0.9533 0.01109 0.00551 -0.0362 0.3051 0.9162 7.250 0.9634 0.01182 0.00602 -0.0333 0.2531 0.9219 7.500 0.9750 0.01254 0.00654 -0.0308 0.2081 0.9288 7.750 0.9847 0.01314 0.00701 -0.0278 0.1722 0.9364 8.000 0.9943 0.01373 0.00749 -0.0249 0.1430 0.9459 8.250 1.0014 0.01422 0.00791 -0.0214 0.1213 0.9587 8.500 1.0170 0.01492 0.00853 -0.0200 0.0989 0.9750 8.750 1.0392 0.01567 0.00921 -0.0202 0.0794 1.0000 9.000 1.0541 0.01642 0.00990 -0.0190 0.0666 1.0000 9.250 1.0686 0.01717 0.01063 -0.0177 0.0578 1.0000 9.500 1.0814 0.01799 0.01141 -0.0162 0.0509 1.0000 9.750 1.0965 0.01868 0.01214 -0.0150 0.0467 1.0000 10.000 1.1095 0.01948 0.01295 -0.0136 0.0432 1.0000 10.250 1.1180 0.02056 0.01405 -0.0118 0.0392 1.0000 10.500 1.1326 0.02131 0.01488 -0.0107 0.0372 1.0000 10.750 1.1454 0.02220 0.01580 -0.0095 0.0343 1.0000 11.000 1.1520 0.02353 0.01715 -0.0079 0.0313 1.0000 11.250 1.1655 0.02445 0.01814 -0.0070 0.0290 1.0000 11.500 1.1778 0.02548 0.01918 -0.0061 0.0256 1.0000 11.750 1.1868 0.02679 0.02053 -0.0051 0.0215 1.0000 12.000 1.1942 0.02826 0.02201 -0.0040 0.0187 1.0000 12.250 1.2009 0.02987 0.02368 -0.0029 0.0158 1.0000 12.500 1.2079 0.03148 0.02534 -0.0020 0.0146 1.0000 12.750 1.2090 0.03366 0.02759 -0.0009 0.0131 1.0000 13.000 1.2154 0.03542 0.02944 -0.0002 0.0125 1.0000 13.250 1.2206 0.03732 0.03142 0.0005 0.0118 1.0000 13.500 1.2253 0.03932 0.03350 0.0010 0.0113 1.0000 13.750 1.2274 0.04161 0.03584 0.0015 0.0107 1.0000 14.000 1.2230 0.04460 0.03892 0.0021 0.0103 1.0000 14.250 1.2231 0.04725 0.04167 0.0025 0.0100 1.0000 14.500 1.2270 0.04957 0.04411 0.0026 0.0097 1.0000 14.750 1.2278 0.05229 0.04695 0.0028 0.0096 1.0000 15.000 1.2288 0.05508 0.04986 0.0027 0.0092 1.0000 15.250 1.2311 0.05779 0.05269 0.0024 0.0089 1.0000 15.500 1.2323 0.06071 0.05571 0.0020 0.0086 1.0000 15.750 1.2315 0.06397 0.05908 0.0015 0.0085 1.0000 16.000 1.2312 0.06726 0.06247 0.0007 0.0083 1.0000 16.250 1.2293 0.07087 0.06617 -0.0002 0.0081 1.0000 16.500 1.2251 0.07487 0.07030 -0.0013 0.0079 1.0000 16.750 1.2204 0.07909 0.07463 -0.0026 0.0078 1.0000 17.000 1.2140 0.08369 0.07935 -0.0041 0.0077 1.0000 17.250 1.2069 0.08853 0.08432 -0.0059 0.0076 1.0000 17.500 1.1965 0.09404 0.08999 -0.0080 0.0074 1.0000 17.750 1.1886 0.09936 0.09546 -0.0104 0.0074 1.0000 18.000 1.1763 0.10561 0.10188 -0.0132 0.0074 1.0000 18.250 1.1639 0.11208 0.10852 -0.0164 0.0073 1.0000 18.500 1.1518 0.11877 0.11537 -0.0200 0.0073 1.0000 18.750 1.1386 0.12592 0.12269 -0.0240 0.0073 1.0000 19.000 1.1228 0.13379 0.13073 -0.0286 0.0073 1.0000 19.250 1.1122 0.14085 0.13793 -0.0330 0.0073 1.0000