XFOIL Version 6.96 Calculated polar for: EPPLER 636 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4297 0.09169 0.08854 -0.0077 1.0000 0.0292 -8.750 -0.4308 0.08763 0.08453 -0.0101 1.0000 0.0298 -8.500 -0.4340 0.08339 0.08034 -0.0131 1.0000 0.0301 -8.250 -0.4418 0.07889 0.07588 -0.0168 0.9398 0.0302 -8.000 -0.4361 0.07333 0.07001 -0.0232 0.8253 0.0309 -7.750 -0.4441 0.06973 0.06619 -0.0232 0.7848 0.0314 -7.500 -0.4492 0.06588 0.06210 -0.0232 0.7583 0.0323 -7.250 -0.4558 0.06216 0.05789 -0.0221 0.7391 0.0334 -7.000 -0.4513 0.05896 0.05443 -0.0206 0.7200 0.0334 -6.500 -0.4485 0.04512 0.04003 -0.0164 0.6937 0.0198 -6.250 -0.4390 0.04175 0.03630 -0.0143 0.6788 0.0199 -6.000 -0.4303 0.03862 0.03287 -0.0123 0.6650 0.0207 -5.750 -0.4128 0.03797 0.03215 -0.0116 0.6493 0.0218 -5.250 -0.3833 0.03064 0.02365 -0.0060 0.6269 0.0199 -5.000 -0.3651 0.02832 0.02097 -0.0043 0.6149 0.0198 -4.750 -0.3448 0.02630 0.01858 -0.0027 0.6032 0.0197 -4.500 -0.3228 0.02450 0.01639 -0.0014 0.5921 0.0197 -4.250 -0.2992 0.02299 0.01453 -0.0003 0.5811 0.0198 -4.000 -0.2742 0.02169 0.01291 0.0006 0.5704 0.0200 -3.750 -0.2484 0.02056 0.01151 0.0014 0.5601 0.0202 -3.500 -0.2224 0.01923 0.01001 0.0018 0.5500 0.0207 -3.250 -0.1967 0.01848 0.00919 0.0023 0.5398 0.0218 -3.000 -0.1707 0.01784 0.00843 0.0028 0.5309 0.0229 -2.750 -0.1447 0.01715 0.00764 0.0033 0.5219 0.0235 -2.500 -0.1192 0.01651 0.00691 0.0040 0.5134 0.0239 -2.250 -0.0945 0.01596 0.00626 0.0048 0.5050 0.0244 -2.000 -0.0700 0.01549 0.00572 0.0056 0.4969 0.0251 -1.750 -0.0457 0.01512 0.00524 0.0065 0.4896 0.0258 -1.500 -0.0213 0.01475 0.00481 0.0073 0.4822 0.0268 -1.250 0.0032 0.01447 0.00445 0.0081 0.4752 0.0286 -1.000 0.0285 0.01428 0.00420 0.0087 0.4681 0.0323 -0.750 0.0534 0.01407 0.00395 0.0095 0.4614 0.0380 -0.500 0.0777 0.01380 0.00373 0.0103 0.4557 0.0631 -0.250 0.0950 0.01286 0.00353 0.0120 0.4498 0.2743 0.250 0.2858 0.01273 0.00519 -0.0128 0.4304 0.9756 0.500 0.3175 0.01275 0.00508 -0.0137 0.4248 0.9787 0.750 0.3471 0.01278 0.00502 -0.0142 0.4188 0.9822 1.000 0.3780 0.01281 0.00492 -0.0150 0.4139 0.9847 1.250 0.4106 0.01279 0.00484 -0.0161 0.4086 0.9870 1.500 0.4420 0.01280 0.00478 -0.0170 0.4034 0.9894 1.750 0.4726 0.01286 0.00472 -0.0177 0.3989 0.9920 2.000 0.5030 0.01289 0.00473 -0.0184 0.3939 0.9943 2.250 0.5348 0.01289 0.00468 -0.0194 0.3889 0.9962 2.500 0.5660 0.01293 0.00465 -0.0204 0.3849 0.9983 2.750 0.5962 0.01298 0.00468 -0.0211 0.3805 1.0000 3.000 0.6201 0.01307 0.00477 -0.0204 0.3761 1.0000 3.250 0.6438 0.01317 0.00483 -0.0197 0.3719 1.0000 3.500 0.6673 0.01331 0.00492 -0.0191 0.3686 1.0000 3.750 0.6913 0.01341 0.00506 -0.0184 0.3645 1.0000 4.000 0.7151 0.01353 0.00519 -0.0178 0.3605 1.0000 4.250 0.7386 0.01366 0.00530 -0.0171 0.3566 1.0000 4.500 0.7622 0.01382 0.00545 -0.0164 0.3531 1.0000 4.750 0.7860 0.01396 0.00565 -0.0158 0.3493 1.0000 5.000 0.8095 0.01411 0.00584 -0.0151 0.3453 1.0000 5.250 0.8329 0.01428 0.00601 -0.0144 0.3416 1.0000 5.500 0.8562 0.01447 0.00621 -0.0137 0.3382 1.0000 5.750 0.8795 0.01465 0.00647 -0.0130 0.3343 1.0000 6.000 0.9026 0.01483 0.00671 -0.0123 0.3302 1.0000 6.250 0.9255 0.01504 0.00694 -0.0115 0.3267 1.0000 6.500 0.9484 0.01527 0.00721 -0.0108 0.3232 1.0000 6.750 0.9711 0.01548 0.00752 -0.0100 0.3188 1.0000 7.000 0.9936 0.01569 0.00779 -0.0092 0.3146 1.0000 7.250 1.0159 0.01594 0.00805 -0.0084 0.3108 1.0000 7.500 1.0381 0.01617 0.00841 -0.0075 0.3057 1.0000 7.750 1.0599 0.01638 0.00871 -0.0066 0.3002 1.0000 8.000 1.0814 0.01664 0.00896 -0.0057 0.2956 1.0000 8.250 1.1029 0.01689 0.00939 -0.0048 0.2899 1.0000 8.500 1.1241 0.01715 0.00972 -0.0038 0.2848 1.0000 8.750 1.1448 0.01744 0.01007 -0.0027 0.2795 1.0000 9.000 1.1654 0.01772 0.01049 -0.0017 0.2731 1.0000 9.250 1.1850 0.01802 0.01083 -0.0005 0.2671 1.0000 9.500 1.2048 0.01833 0.01130 0.0006 0.2595 1.0000 9.750 1.2232 0.01868 0.01169 0.0019 0.2527 1.0000 10.000 1.2417 0.01904 0.01219 0.0032 0.2441 1.0000 10.250 1.2588 0.01945 0.01268 0.0046 0.2354 1.0000 10.500 1.2742 0.01992 0.01321 0.0063 0.2250 1.0000 10.750 1.2880 0.02047 0.01381 0.0081 0.2122 1.0000 11.000 1.2995 0.02112 0.01450 0.0101 0.1976 1.0000 11.250 1.3072 0.02195 0.01532 0.0126 0.1793 1.0000 11.500 1.3110 0.02293 0.01628 0.0155 0.1634 1.0000 11.750 1.3079 0.02414 0.01745 0.0192 0.1478 1.0000 12.000 1.2997 0.02533 0.01865 0.0235 0.1376 1.0000 12.250 1.2878 0.02714 0.02045 0.0268 0.1259 1.0000 12.500 1.2784 0.02940 0.02274 0.0286 0.1174 1.0000 12.750 1.2716 0.03193 0.02534 0.0294 0.1098 1.0000 13.000 1.2600 0.03524 0.02868 0.0296 0.1004 1.0000 13.250 1.2481 0.03883 0.03231 0.0294 0.0936 1.0000 13.500 1.2367 0.04255 0.03607 0.0290 0.0855 1.0000 13.750 1.2247 0.04646 0.04003 0.0284 0.0801 1.0000 14.000 1.2138 0.05032 0.04395 0.0277 0.0746 1.0000 14.250 1.2016 0.05440 0.04810 0.0269 0.0710 1.0000 14.500 1.1900 0.05851 0.05226 0.0260 0.0654 1.0000 14.750 1.1767 0.06292 0.05671 0.0250 0.0610 1.0000 15.000 1.1666 0.06713 0.06099 0.0239 0.0572 1.0000 15.250 1.1568 0.07140 0.06532 0.0227 0.0527 1.0000 15.500 1.1478 0.07569 0.06968 0.0214 0.0503 1.0000 15.750 1.1393 0.07998 0.07404 0.0201 0.0465 1.0000 16.000 1.1303 0.08443 0.07855 0.0187 0.0425 1.0000 16.250 1.1202 0.08914 0.08331 0.0171 0.0390 1.0000 16.500 1.1125 0.09355 0.08779 0.0156 0.0353 1.0000 16.750 1.1021 0.09848 0.09275 0.0139 0.0320 1.0000 17.000 1.0929 0.10330 0.09763 0.0121 0.0276 1.0000