XFOIL Version 6.96 Calculated polar for: S8066 (10% version of S8065 w/ lower surface aer 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.6873 0.06854 0.06632 -0.0357 1.0000 0.0049 -11.000 -0.7288 0.05324 0.05076 -0.0484 1.0000 0.0047 -10.750 -0.7559 0.04694 0.04426 -0.0516 1.0000 0.0047 -10.500 -0.7839 0.04205 0.03914 -0.0512 1.0000 0.0046 -10.250 -0.8018 0.03896 0.03584 -0.0482 1.0000 0.0047 -10.000 -0.8144 0.03535 0.03190 -0.0454 1.0000 0.0046 -9.750 -0.8159 0.03258 0.02883 -0.0430 1.0000 0.0047 -9.500 -0.8174 0.02980 0.02572 -0.0400 1.0000 0.0047 -9.250 -0.8004 0.02702 0.02256 -0.0402 0.9908 0.0048 -9.000 -0.7761 0.02512 0.02037 -0.0411 0.9842 0.0051 -8.750 -0.7525 0.02320 0.01815 -0.0417 0.9777 0.0052 -8.500 -0.7266 0.02160 0.01630 -0.0424 0.9725 0.0054 -8.250 -0.7013 0.02025 0.01473 -0.0427 0.9669 0.0055 -8.000 -0.6765 0.01894 0.01321 -0.0428 0.9611 0.0055 -7.750 -0.6519 0.01777 0.01185 -0.0427 0.9559 0.0056 -7.500 -0.6292 0.01679 0.01073 -0.0421 0.9496 0.0056 -7.250 -0.6059 0.01594 0.00975 -0.0416 0.9443 0.0057 -7.000 -0.5834 0.01519 0.00889 -0.0409 0.9388 0.0057 -6.750 -0.5617 0.01433 0.00792 -0.0400 0.9333 0.0059 -6.500 -0.5393 0.01360 0.00707 -0.0392 0.9288 0.0061 -6.250 -0.5160 0.01301 0.00641 -0.0385 0.9238 0.0064 -6.000 -0.4919 0.01254 0.00586 -0.0379 0.9191 0.0068 -5.750 -0.4675 0.01213 0.00536 -0.0374 0.9152 0.0073 -5.500 -0.4424 0.01176 0.00493 -0.0369 0.9109 0.0079 -5.250 -0.4172 0.01142 0.00451 -0.0365 0.9065 0.0087 -5.000 -0.3922 0.01105 0.00411 -0.0360 0.9025 0.0110 -4.750 -0.3673 0.01065 0.00376 -0.0356 0.8987 0.0221 -4.500 -0.3421 0.01029 0.00347 -0.0352 0.8943 0.0382 -4.250 -0.3167 0.00997 0.00320 -0.0349 0.8901 0.0575 -4.000 -0.2910 0.00970 0.00297 -0.0346 0.8865 0.0767 -3.750 -0.2654 0.00937 0.00276 -0.0343 0.8820 0.1071 -3.500 -0.2405 0.00896 0.00255 -0.0340 0.8774 0.1552 -3.250 -0.2158 0.00853 0.00232 -0.0336 0.8733 0.2185 -3.000 -0.1914 0.00805 0.00213 -0.0333 0.8690 0.2951 -2.750 -0.1669 0.00762 0.00196 -0.0329 0.8639 0.3739 -2.500 -0.1419 0.00726 0.00183 -0.0325 0.8594 0.4427 -2.250 -0.1162 0.00700 0.00172 -0.0321 0.8549 0.4976 -2.000 -0.0903 0.00678 0.00164 -0.0318 0.8495 0.5449 -1.750 -0.0643 0.00659 0.00157 -0.0315 0.8446 0.5873 -1.500 -0.0382 0.00642 0.00152 -0.0311 0.8395 0.6298 -1.250 -0.0120 0.00629 0.00151 -0.0307 0.8335 0.6688 -1.000 0.0146 0.00621 0.00150 -0.0303 0.8283 0.7006 -0.750 0.0416 0.00616 0.00151 -0.0301 0.8214 0.7264 -0.500 0.0686 0.00612 0.00149 -0.0298 0.8149 0.7462 -0.250 0.0958 0.00609 0.00150 -0.0296 0.8072 0.7618 0.000 0.1229 0.00607 0.00148 -0.0293 0.7991 0.7745 0.250 0.1503 0.00606 0.00147 -0.0291 0.7884 0.7849 0.500 0.1775 0.00605 0.00145 -0.0289 0.7766 0.7942 0.750 0.2046 0.00605 0.00144 -0.0286 0.7628 0.8026 1.000 0.2315 0.00607 0.00143 -0.0284 0.7466 0.8112 1.250 0.2580 0.00611 0.00143 -0.0280 0.7282 0.8189 1.750 0.3106 0.00626 0.00147 -0.0272 0.6811 0.8344 2.000 0.3364 0.00638 0.00152 -0.0267 0.6516 0.8422 2.250 0.3611 0.00656 0.00159 -0.0260 0.6139 0.8497 2.500 0.3855 0.00679 0.00167 -0.0253 0.5679 0.8577 2.750 0.4093 0.00705 0.00178 -0.0246 0.5188 0.8661 3.000 0.4329 0.00735 0.00193 -0.0238 0.4682 0.8748 3.250 0.4554 0.00776 0.00211 -0.0229 0.4021 0.8848 3.500 0.4775 0.00821 0.00233 -0.0220 0.3361 0.8953 3.750 0.4990 0.00874 0.00259 -0.0210 0.2610 0.9072 4.000 0.5214 0.00925 0.00287 -0.0202 0.1981 0.9207 4.500 0.5758 0.01004 0.00341 -0.0205 0.1217 0.9506 4.750 0.6079 0.01045 0.00373 -0.0217 0.0937 0.9647 5.000 0.6407 0.01085 0.00405 -0.0232 0.0736 0.9784 5.250 0.6732 0.01122 0.00436 -0.0245 0.0585 0.9901 5.500 0.7057 0.01160 0.00470 -0.0259 0.0465 0.9992 5.750 0.7282 0.01194 0.00501 -0.0251 0.0387 1.0000 6.000 0.7505 0.01224 0.00531 -0.0242 0.0334 1.0000 6.250 0.7727 0.01260 0.00566 -0.0234 0.0284 1.0000 6.500 0.7956 0.01292 0.00600 -0.0226 0.0249 1.0000 6.750 0.8179 0.01332 0.00639 -0.0218 0.0202 1.0000 7.000 0.8403 0.01374 0.00683 -0.0210 0.0157 1.0000 7.250 0.8622 0.01422 0.00731 -0.0201 0.0120 1.0000 7.500 0.8839 0.01474 0.00785 -0.0192 0.0101 1.0000 7.750 0.9057 0.01524 0.00840 -0.0183 0.0090 1.0000 8.000 0.9270 0.01580 0.00900 -0.0174 0.0083 1.0000 8.250 0.9474 0.01646 0.00974 -0.0163 0.0077 1.0000 8.500 0.9675 0.01715 0.01051 -0.0152 0.0074 1.0000 8.750 0.9876 0.01781 0.01127 -0.0141 0.0071 1.0000 9.000 1.0069 0.01854 0.01210 -0.0130 0.0069 1.0000 9.250 1.0257 0.01931 0.01296 -0.0118 0.0067 1.0000 9.500 1.0437 0.02013 0.01388 -0.0105 0.0064 1.0000 9.750 1.0606 0.02103 0.01490 -0.0090 0.0063 1.0000 10.000 1.0768 0.02196 0.01595 -0.0075 0.0060 1.0000 10.250 1.0916 0.02298 0.01709 -0.0059 0.0060 1.0000 10.500 1.1050 0.02402 0.01826 -0.0041 0.0058 1.0000 10.750 1.1154 0.02513 0.01948 -0.0018 0.0056 1.0000 11.000 1.1243 0.02631 0.02079 0.0005 0.0055 1.0000 11.250 1.1316 0.02761 0.02222 0.0029 0.0054 1.0000 11.500 1.1371 0.02909 0.02385 0.0052 0.0053 1.0000 11.750 1.1350 0.03130 0.02625 0.0081 0.0051 1.0000 12.000 1.1338 0.03346 0.02862 0.0105 0.0051 1.0000 12.250 1.1336 0.03553 0.03088 0.0125 0.0050 1.0000 12.500 1.1353 0.03741 0.03293 0.0140 0.0049 1.0000 12.750 1.1358 0.03947 0.03518 0.0153 0.0049 1.0000 13.000 1.1302 0.04229 0.03820 0.0164 0.0048 1.0000 13.250 1.1204 0.04575 0.04187 0.0170 0.0048 1.0000 13.500 1.1075 0.04988 0.04622 0.0169 0.0048 1.0000 13.750 1.0974 0.05405 0.05057 0.0159 0.0048 1.0000 14.000 1.0852 0.05893 0.05564 0.0139 0.0047 1.0000 14.250 1.0654 0.06564 0.06253 0.0105 0.0048 1.0000 14.500 1.0478 0.07288 0.06995 0.0060 0.0048 1.0000 14.750 1.0219 0.08284 0.08011 -0.0005 0.0048 1.0000 15.000 0.9984 0.09347 0.09089 -0.0073 0.0048 1.0000 15.250 0.9675 0.10627 0.10380 -0.0148 0.0050 1.0000 15.500 0.9237 0.12277 0.12043 -0.0238 0.0050 1.0000 15.750 0.8767 0.14115 0.13893 -0.0330 0.0052 1.0000