XFOIL Version 6.96 Calculated polar for: Gottingen 765 airfoil (recovered). Thick: .144 L 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.9369 0.12533 0.12213 -0.0054 1.0000 0.0190 -18.750 -0.9761 0.11360 0.11024 -0.0124 1.0000 0.0191 -18.500 -1.0143 0.10275 0.09922 -0.0188 1.0000 0.0191 -18.250 -1.0507 0.09261 0.08892 -0.0247 1.0000 0.0190 -18.000 -1.0839 0.08309 0.07924 -0.0304 1.0000 0.0191 -17.750 -1.1160 0.07371 0.06968 -0.0361 1.0000 0.0190 -17.500 -1.1392 0.06569 0.06148 -0.0413 1.0000 0.0192 -17.250 -1.1595 0.05854 0.05415 -0.0458 1.0000 0.0192 -17.000 -1.1724 0.05317 0.04863 -0.0488 1.0000 0.0193 -16.750 -1.1823 0.04879 0.04409 -0.0506 1.0000 0.0195 -16.500 -1.1900 0.04516 0.04032 -0.0515 1.0000 0.0196 -16.250 -1.1941 0.04225 0.03729 -0.0516 1.0000 0.0199 -16.000 -1.1971 0.03970 0.03461 -0.0511 1.0000 0.0200 -15.750 -1.1985 0.03748 0.03227 -0.0502 1.0000 0.0202 -15.500 -1.1973 0.03561 0.03026 -0.0489 1.0000 0.0204 -15.250 -1.1954 0.03389 0.02843 -0.0474 1.0000 0.0206 -15.000 -1.1937 0.03228 0.02674 -0.0456 1.0000 0.0208 -14.750 -1.1907 0.03083 0.02521 -0.0436 1.0000 0.0210 -14.500 -1.1857 0.02956 0.02388 -0.0416 1.0000 0.0213 -14.250 -1.1772 0.02854 0.02281 -0.0397 1.0000 0.0216 -14.000 -1.1687 0.02755 0.02174 -0.0377 1.0000 0.0220 -13.750 -1.1590 0.02664 0.02076 -0.0356 1.0000 0.0223 -13.500 -1.1487 0.02577 0.01982 -0.0335 1.0000 0.0227 -13.250 -1.1373 0.02497 0.01895 -0.0315 1.0000 0.0231 -13.000 -1.1247 0.02424 0.01813 -0.0295 1.0000 0.0235 -12.750 -1.1121 0.02351 0.01733 -0.0274 1.0000 0.0238 -12.500 -1.0994 0.02279 0.01654 -0.0253 1.0000 0.0242 -12.250 -1.0869 0.02206 0.01578 -0.0231 1.0000 0.0246 -12.000 -1.0727 0.02143 0.01511 -0.0211 1.0000 0.0251 -11.750 -1.0572 0.02086 0.01450 -0.0192 1.0000 0.0256 -11.500 -1.0407 0.02034 0.01394 -0.0174 1.0000 0.0262 -11.250 -1.0242 0.01982 0.01337 -0.0155 1.0000 0.0268 -11.000 -1.0068 0.01935 0.01284 -0.0138 1.0000 0.0274 -10.750 -0.9709 0.01862 0.01207 -0.0161 0.9465 0.0283 -10.500 -0.9334 0.01799 0.01135 -0.0185 0.9134 0.0292 -10.250 -0.9122 0.01761 0.01086 -0.0174 0.8866 0.0300 -10.000 -0.8939 0.01727 0.01040 -0.0155 0.8668 0.0309 -9.750 -0.8752 0.01695 0.00997 -0.0138 0.8514 0.0317 -9.500 -0.8571 0.01656 0.00952 -0.0119 0.8375 0.0328 -9.250 -0.8377 0.01622 0.00913 -0.0103 0.8252 0.0339 -9.000 -0.8177 0.01591 0.00874 -0.0087 0.8142 0.0351 -8.750 -0.7974 0.01562 0.00836 -0.0072 0.8034 0.0363 -8.500 -0.7769 0.01527 0.00798 -0.0057 0.7934 0.0375 -8.000 -0.7344 0.01471 0.00731 -0.0030 0.7744 0.0406 -7.750 -0.7128 0.01445 0.00698 -0.0017 0.7657 0.0423 -7.500 -0.6907 0.01416 0.00669 -0.0005 0.7567 0.0444 -7.250 -0.6682 0.01393 0.00640 0.0006 0.7481 0.0467 -7.000 -0.6454 0.01366 0.00611 0.0017 0.7399 0.0490 -6.750 -0.6224 0.01342 0.00584 0.0027 0.7311 0.0517 -6.500 -0.5988 0.01320 0.00557 0.0037 0.7232 0.0544 -6.250 -0.5753 0.01296 0.00532 0.0046 0.7145 0.0579 -6.000 -0.5514 0.01276 0.00508 0.0055 0.7067 0.0616 -5.750 -0.5276 0.01252 0.00485 0.0064 0.6978 0.0660 -5.500 -0.5036 0.01234 0.00462 0.0073 0.6900 0.0707 -5.250 -0.4793 0.01212 0.00442 0.0081 0.6812 0.0762 -5.000 -0.4553 0.01194 0.00421 0.0090 0.6725 0.0821 -4.750 -0.4308 0.01175 0.00403 0.0098 0.6638 0.0889 -4.500 -0.4067 0.01156 0.00384 0.0106 0.6551 0.0969 -4.250 -0.3821 0.01138 0.00367 0.0114 0.6470 0.1052 -4.000 -0.3576 0.01122 0.00351 0.0122 0.6383 0.1153 -3.750 -0.3331 0.01105 0.00336 0.0130 0.6305 0.1271 -3.500 -0.3087 0.01087 0.00321 0.0138 0.6221 0.1408 -3.250 -0.2843 0.01071 0.00308 0.0146 0.6145 0.1553 -3.000 -0.2598 0.01054 0.00296 0.0154 0.6062 0.1724 -2.750 -0.2357 0.01039 0.00284 0.0162 0.5978 0.1915 -2.500 -0.2114 0.01021 0.00273 0.0170 0.5893 0.2132 -2.000 -0.1633 0.00988 0.00254 0.0187 0.5723 0.2641 -1.750 -0.1399 0.00972 0.00245 0.0197 0.5635 0.2950 -1.500 -0.1167 0.00952 0.00237 0.0207 0.5550 0.3292 -1.250 -0.0950 0.00929 0.00227 0.0220 0.5461 0.3757 -1.000 -0.0764 0.00891 0.00217 0.0239 0.5377 0.4485 -0.750 -0.0667 0.00833 0.00203 0.0277 0.5296 0.5687 -0.500 -0.0602 0.00777 0.00194 0.0323 0.5220 0.6901 -0.250 -0.0368 0.00742 0.00203 0.0337 0.5125 0.8019 0.000 0.0106 0.00749 0.00220 0.0298 0.5017 0.8497 0.250 0.0564 0.00768 0.00237 0.0263 0.4903 0.8744 0.500 0.0951 0.00787 0.00253 0.0242 0.4794 0.8874 0.750 0.1225 0.00803 0.00264 0.0246 0.4700 0.8978 1.000 0.1570 0.00826 0.00281 0.0234 0.4585 0.9045 1.750 0.2513 0.00890 0.00330 0.0218 0.4276 0.9195 2.000 0.2673 0.00902 0.00338 0.0245 0.4193 0.9276 2.250 0.3066 0.00929 0.00359 0.0223 0.4084 0.9290 2.500 0.3443 0.00954 0.00380 0.0203 0.3983 0.9307 2.750 0.3773 0.00973 0.00393 0.0193 0.3883 0.9323 3.000 0.4074 0.00986 0.00403 0.0188 0.3789 0.9341 3.500 0.4473 0.01005 0.00415 0.0221 0.3627 0.9425 3.750 0.4793 0.01020 0.00427 0.0212 0.3538 0.9432 4.000 0.5110 0.01033 0.00438 0.0203 0.3455 0.9440 4.250 0.5415 0.01050 0.00450 0.0197 0.3364 0.9449 4.500 0.5723 0.01064 0.00462 0.0190 0.3282 0.9460 4.750 0.6019 0.01081 0.00476 0.0185 0.3195 0.9473 5.000 0.6307 0.01095 0.00490 0.0182 0.3111 0.9489 5.250 0.6570 0.01113 0.00504 0.0183 0.3022 0.9509 5.500 0.6793 0.01127 0.00518 0.0194 0.2947 0.9541 5.750 0.6994 0.01144 0.00533 0.0209 0.2864 0.9573 6.000 0.7296 0.01162 0.00549 0.0202 0.2768 0.9580 6.250 0.7591 0.01184 0.00568 0.0196 0.2666 0.9589 6.500 0.7887 0.01205 0.00587 0.0190 0.2563 0.9600 6.750 0.8173 0.01229 0.00609 0.0186 0.2462 0.9613 7.000 0.8440 0.01256 0.00632 0.0185 0.2353 0.9629 7.250 0.8691 0.01281 0.00655 0.0187 0.2240 0.9648 7.500 0.8908 0.01309 0.00681 0.0197 0.2140 0.9675 7.750 0.9092 0.01340 0.00709 0.0213 0.2036 0.9706 8.000 0.9374 0.01374 0.00739 0.0207 0.1911 0.9715 8.250 0.9647 0.01409 0.00771 0.0203 0.1793 0.9725 8.500 0.9907 0.01448 0.00807 0.0201 0.1671 0.9738 8.750 1.0155 0.01491 0.00845 0.0201 0.1553 0.9755 9.000 1.0386 0.01539 0.00889 0.0203 0.1431 0.9776 9.250 1.0576 0.01588 0.00934 0.0214 0.1328 0.9804 9.500 1.0749 0.01635 0.00980 0.0229 0.1233 0.9828 9.750 1.0998 0.01688 0.01030 0.0225 0.1129 0.9840 10.000 1.1236 0.01747 0.01085 0.0223 0.1029 0.9855 10.250 1.1455 0.01808 0.01145 0.0224 0.0944 0.9874 10.500 1.1637 0.01872 0.01207 0.0231 0.0864 0.9897 10.750 1.1772 0.01930 0.01266 0.0248 0.0807 0.9924 11.000 1.1917 0.02001 0.01338 0.0258 0.0744 0.9945 11.250 1.2086 0.02085 0.01422 0.0259 0.0681 0.9967 11.500 1.2252 0.02171 0.01510 0.0260 0.0637 0.9986 11.750 1.2384 0.02282 0.01622 0.0263 0.0590 1.0000 12.000 1.2377 0.02378 0.01723 0.0294 0.0564 1.0000 12.250 1.2363 0.02493 0.01841 0.0324 0.0537 1.0000 12.500 1.2352 0.02620 0.01971 0.0350 0.0513 1.0000 12.750 1.2357 0.02749 0.02104 0.0372 0.0488 1.0000 13.000 1.2357 0.02894 0.02253 0.0392 0.0469 1.0000 13.250 1.2355 0.03052 0.02415 0.0410 0.0451 1.0000 13.500 1.2365 0.03211 0.02580 0.0425 0.0434 1.0000 13.750 1.2362 0.03391 0.02764 0.0439 0.0416 1.0000 14.000 1.2349 0.03590 0.02968 0.0451 0.0402 1.0000 14.250 1.2346 0.03789 0.03173 0.0461 0.0389 1.0000 14.500 1.2341 0.04000 0.03391 0.0468 0.0375 1.0000 14.750 1.2317 0.04236 0.03632 0.0475 0.0359 1.0000 15.000 1.2284 0.04493 0.03894 0.0479 0.0351 1.0000 15.250 1.2260 0.04752 0.04161 0.0482 0.0341 1.0000 15.500 1.2241 0.05015 0.04432 0.0483 0.0330 1.0000 15.750 1.2205 0.05309 0.04732 0.0482 0.0320 1.0000 16.000 1.2161 0.05621 0.05051 0.0479 0.0312 1.0000 16.250 1.2093 0.05971 0.05407 0.0474 0.0303 1.0000 16.500 1.2052 0.06298 0.05742 0.0469 0.0298 1.0000 16.750 1.2007 0.06637 0.06090 0.0463 0.0290 1.0000 17.000 1.1951 0.06997 0.06458 0.0455 0.0283 1.0000 17.250 1.1884 0.07379 0.06848 0.0445 0.0277 1.0000 17.500 1.1808 0.07781 0.07257 0.0434 0.0271 1.0000 17.750 1.1723 0.08201 0.07685 0.0422 0.0265 1.0000 18.000 1.1633 0.08637 0.08128 0.0409 0.0262 1.0000