XFOIL Version 6.96 Calculated polar for: GOE 647 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -0.6563 0.08046 0.07806 -0.0723 1.0000 0.0246 -15.500 -0.7216 0.06718 0.06455 -0.0815 1.0000 0.0246 -15.250 -0.7578 0.05902 0.05623 -0.0870 1.0000 0.0246 -15.000 -0.7835 0.05273 0.04983 -0.0910 1.0000 0.0246 -14.750 -0.8064 0.04703 0.04399 -0.0947 1.0000 0.0246 -14.500 -0.8233 0.04236 0.03921 -0.0978 1.0000 0.0247 -14.250 -0.8477 0.03767 0.03438 -0.1002 1.0000 0.0247 -14.000 -0.8594 0.03154 0.02801 -0.1081 0.9966 0.0250 -13.750 -0.8435 0.02917 0.02553 -0.1113 0.9920 0.0253 -13.500 -0.8250 0.02772 0.02402 -0.1124 0.9866 0.0255 -13.250 -0.7990 0.02647 0.02273 -0.1142 0.9830 0.0258 -13.000 -0.7743 0.02529 0.02148 -0.1154 0.9785 0.0260 -12.750 -0.7496 0.02432 0.02044 -0.1163 0.9729 0.0263 -12.500 -0.7208 0.02329 0.01932 -0.1178 0.9694 0.0267 -12.250 -0.6933 0.02240 0.01836 -0.1189 0.9631 0.0270 -12.000 -0.6609 0.02155 0.01741 -0.1207 0.9579 0.0275 -11.750 -0.6263 0.02058 0.01634 -0.1230 0.9531 0.0278 -11.500 -0.5973 0.01978 0.01543 -0.1240 0.9427 0.0281 -11.250 -0.5667 0.01915 0.01469 -0.1250 0.9323 0.0283 -11.000 -0.5400 0.01843 0.01383 -0.1254 0.9198 0.0286 -10.750 -0.5229 0.01712 0.01240 -0.1242 0.9051 0.0291 -10.500 -0.5024 0.01654 0.01175 -0.1231 0.8914 0.0294 -10.250 -0.4806 0.01612 0.01128 -0.1221 0.8792 0.0298 -10.000 -0.4584 0.01574 0.01081 -0.1210 0.8674 0.0302 -9.750 -0.4367 0.01535 0.01035 -0.1199 0.8558 0.0305 -9.500 -0.4149 0.01492 0.00984 -0.1188 0.8452 0.0309 -9.250 -0.3925 0.01457 0.00939 -0.1177 0.8338 0.0313 -9.000 -0.3698 0.01419 0.00895 -0.1166 0.8233 0.0316 -8.750 -0.3473 0.01385 0.00851 -0.1155 0.8112 0.0320 -8.500 -0.3245 0.01355 0.00811 -0.1143 0.7973 0.0323 -8.250 -0.3009 0.01331 0.00777 -0.1133 0.7830 0.0326 -8.000 -0.2796 0.01282 0.00719 -0.1120 0.7692 0.0330 -7.750 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0.2694 0.00878 0.00225 -0.0952 0.5263 0.1206 -2.250 0.2940 0.00857 0.00218 -0.0944 0.5164 0.1661 -2.000 0.3190 0.00851 0.00217 -0.0937 0.5050 0.1986 -1.750 0.3450 0.00850 0.00216 -0.0931 0.4922 0.2152 -1.500 0.3708 0.00852 0.00216 -0.0925 0.4797 0.2283 -1.250 0.3963 0.00857 0.00216 -0.0919 0.4667 0.2393 -1.000 0.4213 0.00862 0.00218 -0.0912 0.4531 0.2519 -0.750 0.4470 0.00866 0.00219 -0.0906 0.4400 0.2623 -0.500 0.4722 0.00872 0.00222 -0.0899 0.4270 0.2763 -0.250 0.4967 0.00876 0.00226 -0.0891 0.4141 0.2976 0.000 0.5207 0.00881 0.00232 -0.0882 0.4004 0.3228 0.250 0.5452 0.00886 0.00237 -0.0874 0.3878 0.3457 0.500 0.5698 0.00891 0.00244 -0.0867 0.3771 0.3689 0.750 0.5935 0.00899 0.00252 -0.0858 0.3663 0.3962 1.000 0.6184 0.00903 0.00259 -0.0851 0.3581 0.4235 1.250 0.6421 0.00913 0.00269 -0.0842 0.3494 0.4484 1.500 0.6671 0.00916 0.00276 -0.0834 0.3434 0.4726 1.750 0.6909 0.00924 0.00285 -0.0826 0.3367 0.4961 2.000 0.7144 0.00929 0.00295 -0.0816 0.3308 0.5248 2.250 0.7372 0.00924 0.00304 -0.0806 0.3261 0.5759 2.500 0.7532 0.00898 0.00317 -0.0781 0.3215 0.7236 2.750 0.8659 0.00891 0.00358 -0.0964 0.3121 0.9893 3.000 0.9073 0.00910 0.00373 -0.0993 0.3074 1.0000 3.250 0.9288 0.00927 0.00384 -0.0980 0.3034 1.0000 3.500 0.9492 0.00947 0.00399 -0.0965 0.2987 1.0000 3.750 0.9724 0.00956 0.00408 -0.0954 0.2966 1.0000 4.000 0.9949 0.00969 0.00419 -0.0943 0.2938 1.0000 4.250 1.0169 0.00983 0.00430 -0.0931 0.2907 1.0000 4.500 1.0380 0.01001 0.00445 -0.0918 0.2874 1.0000 4.750 1.0580 0.01023 0.00462 -0.0902 0.2835 1.0000 5.000 1.0798 0.01037 0.00477 -0.0890 0.2812 1.0000 5.250 1.1023 0.01050 0.00490 -0.0879 0.2792 1.0000 5.500 1.1242 0.01065 0.00504 -0.0868 0.2767 1.0000 5.750 1.1448 0.01082 0.00520 -0.0854 0.2738 1.0000 6.000 1.1630 0.01102 0.00537 -0.0835 0.2710 1.0000 6.250 1.1792 0.01127 0.00559 -0.0813 0.2675 1.0000 6.500 1.1982 0.01145 0.00578 -0.0796 0.2655 1.0000 6.750 1.2190 0.01160 0.00594 -0.0783 0.2639 1.0000 7.000 1.2396 0.01177 0.00612 -0.0770 0.2620 1.0000 7.250 1.2599 0.01196 0.00632 -0.0757 0.2600 1.0000 7.500 1.2796 0.01219 0.00654 -0.0743 0.2578 1.0000 7.750 1.2987 0.01245 0.00679 -0.0728 0.2554 1.0000 8.000 1.3163 0.01277 0.00710 -0.0712 0.2527 1.0000 8.250 1.3341 0.01311 0.00744 -0.0696 0.2503 1.0000 8.500 1.3556 0.01331 0.00768 -0.0687 0.2492 1.0000 8.750 1.3765 0.01355 0.00794 -0.0677 0.2477 1.0000 9.000 1.3971 0.01380 0.00821 -0.0667 0.2459 1.0000 9.250 1.4171 0.01408 0.00851 -0.0657 0.2441 1.0000 9.500 1.4361 0.01442 0.00886 -0.0645 0.2423 1.0000 9.750 1.4545 0.01479 0.00924 -0.0633 0.2405 1.0000 10.000 1.4711 0.01526 0.00971 -0.0619 0.2382 1.0000 10.250 1.4856 0.01585 0.01030 -0.0602 0.2354 1.0000 10.500 1.5073 0.01609 0.01059 -0.0596 0.2340 1.0000 10.750 1.5274 0.01643 0.01097 -0.0588 0.2324 1.0000 11.000 1.5468 0.01680 0.01138 -0.0580 0.2306 1.0000 11.250 1.5652 0.01723 0.01183 -0.0570 0.2284 1.0000 11.500 1.5823 0.01775 0.01237 -0.0560 0.2265 1.0000 11.750 1.5978 0.01837 0.01299 -0.0548 0.2242 1.0000 12.000 1.6096 0.01920 0.01382 -0.0533 0.2206 1.0000 12.250 1.6300 0.01957 0.01425 -0.0528 0.2191 1.0000 12.500 1.6490 0.02004 0.01476 -0.0522 0.2168 1.0000 12.750 1.6661 0.02061 0.01537 -0.0514 0.2141 1.0000 13.000 1.6810 0.02133 0.01612 -0.0504 0.2118 1.0000 13.250 1.6935 0.02223 0.01702 -0.0493 0.2089 1.0000 13.500 1.7049 0.02321 0.01803 -0.0481 0.2060 1.0000 13.750 1.7226 0.02381 0.01869 -0.0476 0.2044 1.0000 14.000 1.7385 0.02453 0.01947 -0.0469 0.2021 1.0000 14.250 1.7520 0.02542 0.02039 -0.0461 0.1990 1.0000 14.500 1.7619 0.02660 0.02157 -0.0451 0.1954 1.0000 14.750 1.7697 0.02796 0.02296 -0.0441 0.1924 1.0000 15.000 1.7856 0.02874 0.02381 -0.0436 0.1900 1.0000 15.250 1.7971 0.02986 0.02497 -0.0429 0.1862 1.0000 15.500 1.8043 0.03137 0.02649 -0.0420 0.1822 1.0000 15.750 1.8110 0.03294 0.02810 -0.0412 0.1781 1.0000 16.000 1.8203 0.03434 0.02955 -0.0406 0.1735 1.0000 16.250 1.8203 0.03658 0.03178 -0.0397 0.1670 1.0000 16.500 1.8248 0.03848 0.03372 -0.0391 0.1608 1.0000 16.750 1.8202 0.04127 0.03650 -0.0383 0.1531 1.0000 17.000 1.8123 0.04446 0.03969 -0.0376 0.1431 1.0000 17.250 1.7939 0.04880 0.04400 -0.0369 0.1312 1.0000 17.500 1.7771 0.05316 0.04836 -0.0366 0.1216 1.0000 17.750 1.7570 0.05798 0.05320 -0.0364 0.1130 1.0000 18.000 1.7326 0.06349 0.05875 -0.0365 0.1053 1.0000 18.250 1.7087 0.06910 0.06440 -0.0368 0.0986 1.0000 18.500 1.6830 0.07513 0.07050 -0.0375 0.0920 1.0000 18.750 1.6575 0.08131 0.07673 -0.0384 0.0874 1.0000 19.000 1.6267 0.08829 0.08378 -0.0396 0.0810 1.0000