XFOIL Version 6.96 Calculated polar for: GOE 617 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.9574 0.10686 0.10423 -0.0431 1.0000 0.0118 -18.750 -1.1183 0.07551 0.07238 -0.0614 1.0000 0.0108 -18.500 -1.1792 0.06162 0.05821 -0.0702 1.0000 0.0106 -18.250 -1.2120 0.05306 0.04945 -0.0757 1.0000 0.0106 -18.000 -1.2313 0.04710 0.04333 -0.0792 1.0000 0.0106 -17.750 -1.2438 0.04260 0.03869 -0.0813 1.0000 0.0107 -17.500 -1.2520 0.03903 0.03500 -0.0824 1.0000 0.0108 -17.250 -1.2582 0.03604 0.03191 -0.0827 1.0000 0.0111 -17.000 -1.2614 0.03362 0.02939 -0.0823 1.0000 0.0114 -16.750 -1.2620 0.03164 0.02732 -0.0814 1.0000 0.0116 -16.500 -1.2604 0.02999 0.02559 -0.0801 1.0000 0.0119 -16.250 -1.2576 0.02854 0.02406 -0.0785 1.0000 0.0122 -16.000 -1.2539 0.02727 0.02271 -0.0767 1.0000 0.0126 -15.750 -1.2488 0.02617 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-0.0332 0.5415 0.2139 -0.500 0.1522 0.00816 0.00153 -0.0323 0.5285 0.2327 -0.250 0.1710 0.00777 0.00146 -0.0306 0.5181 0.3370 0.000 0.1933 0.00762 0.00145 -0.0294 0.5105 0.3915 0.250 0.2166 0.00750 0.00145 -0.0285 0.5025 0.4309 0.500 0.2394 0.00741 0.00145 -0.0274 0.4948 0.4702 0.750 0.2608 0.00725 0.00145 -0.0260 0.4857 0.5250 1.000 0.2818 0.00714 0.00146 -0.0245 0.4752 0.5759 1.250 0.2999 0.00697 0.00147 -0.0224 0.4640 0.6445 1.500 0.3177 0.00679 0.00149 -0.0202 0.4537 0.7101 1.750 0.3358 0.00668 0.00153 -0.0180 0.4430 0.7644 2.000 0.3554 0.00662 0.00159 -0.0161 0.4324 0.8126 2.250 0.3781 0.00660 0.00168 -0.0149 0.4227 0.8547 2.500 0.4039 0.00666 0.00178 -0.0143 0.4126 0.8815 2.750 0.4311 0.00676 0.00187 -0.0142 0.4007 0.8975 3.000 0.4575 0.00690 0.00197 -0.0138 0.3848 0.9096 3.250 0.4885 0.00708 0.00211 -0.0146 0.3677 0.9219 3.500 0.5191 0.00730 0.00225 -0.0153 0.3488 0.9310 3.750 0.5494 0.00753 0.00241 -0.0159 0.3295 0.9407 4.000 0.5857 0.00777 0.00259 -0.0179 0.3143 0.9474 4.250 0.6148 0.00800 0.00277 -0.0182 0.3004 0.9562 4.500 0.6504 0.00831 0.00298 -0.0201 0.2773 0.9600 4.750 0.6839 0.00868 0.00322 -0.0216 0.2515 0.9636 5.000 0.7088 0.00909 0.00348 -0.0212 0.2184 0.9685 5.250 0.7322 0.00964 0.00382 -0.0206 0.1789 0.9722 5.500 0.7626 0.00997 0.00407 -0.0215 0.1644 0.9735 5.750 0.7925 0.01021 0.00428 -0.0221 0.1571 0.9749 6.000 0.8210 0.01047 0.00450 -0.0225 0.1498 0.9766 6.250 0.8492 0.01065 0.00469 -0.0228 0.1456 0.9786 6.500 0.8733 0.01089 0.00490 -0.0222 0.1399 0.9817 6.750 0.8997 0.01114 0.00513 -0.0222 0.1328 0.9836 7.000 0.9296 0.01139 0.00536 -0.0229 0.1258 0.9846 7.250 0.9585 0.01168 0.00561 -0.0235 0.1179 0.9859 7.500 0.9861 0.01199 0.00587 -0.0239 0.1086 0.9874 7.750 1.0127 0.01230 0.00615 -0.0240 0.1000 0.9891 8.000 1.0382 0.01264 0.00645 -0.0239 0.0928 0.9912 8.250 1.0625 0.01296 0.00675 -0.0236 0.0881 0.9933 8.500 1.0887 0.01332 0.00707 -0.0237 0.0816 0.9948 8.750 1.1148 0.01364 0.00739 -0.0239 0.0772 0.9964 9.000 1.1397 0.01401 0.00773 -0.0239 0.0725 0.9981 9.250 1.1663 0.01430 0.00804 -0.0241 0.0701 0.9993 9.500 1.1858 0.01458 0.00833 -0.0229 0.0679 1.0000 9.750 1.1914 0.01483 0.00860 -0.0188 0.0658 1.0000 10.000 1.1984 0.01514 0.00891 -0.0150 0.0638 1.0000 10.250 1.2068 0.01548 0.00927 -0.0116 0.0616 1.0000 10.500 1.2178 0.01580 0.00961 -0.0088 0.0604 1.0000 10.750 1.2293 0.01616 0.00999 -0.0062 0.0585 1.0000 11.000 1.2405 0.01657 0.01043 -0.0036 0.0566 1.0000 11.250 1.2519 0.01702 0.01089 -0.0011 0.0551 1.0000 11.500 1.2620 0.01757 0.01144 0.0014 0.0524 1.0000 11.750 1.2746 0.01805 0.01195 0.0034 0.0510 1.0000 12.000 1.2868 0.01859 0.01252 0.0055 0.0492 1.0000 12.250 1.2979 0.01923 0.01318 0.0075 0.0467 1.0000 12.500 1.3080 0.01996 0.01392 0.0095 0.0442 1.0000 12.750 1.3193 0.02067 0.01465 0.0113 0.0411 1.0000 13.000 1.3278 0.02160 0.01557 0.0133 0.0372 1.0000 13.250 1.3339 0.02272 0.01666 0.0153 0.0308 1.0000 13.500 1.3324 0.02441 0.01829 0.0178 0.0209 1.0000 13.750 1.3364 0.02583 0.01974 0.0196 0.0176 1.0000 14.000 1.3404 0.02733 0.02127 0.0212 0.0153 1.0000 14.250 1.3465 0.02874 0.02272 0.0225 0.0141 1.0000 14.500 1.3518 0.03027 0.02431 0.0237 0.0132 1.0000 14.750 1.3574 0.03185 0.02593 0.0247 0.0125 1.0000 15.000 1.3632 0.03347 0.02762 0.0256 0.0119 1.0000 15.250 1.3686 0.03518 0.02939 0.0263 0.0115 1.0000 15.500 1.3724 0.03711 0.03138 0.0270 0.0110 1.0000 15.750 1.3757 0.03914 0.03347 0.0275 0.0106 1.0000 16.000 1.3770 0.04147 0.03587 0.0279 0.0101 1.0000 16.250 1.3804 0.04365 0.03812 0.0281 0.0098 1.0000 16.500 1.3830 0.04595 0.04050 0.0282 0.0095 1.0000 16.750 1.3845 0.04845 0.04307 0.0281 0.0093 1.0000 17.000 1.3850 0.05111 0.04581 0.0280 0.0092 1.0000 17.250 1.3836 0.05406 0.04884 0.0277 0.0088 1.0000 17.500 1.3817 0.05711 0.05197 0.0273 0.0086 1.0000 17.750 1.3796 0.06026 0.05519 0.0268 0.0085 1.0000 18.000 1.3759 0.06369 0.05870 0.0261 0.0083 1.0000 18.250 1.3699 0.06746 0.06256 0.0252 0.0081 1.0000 18.500 1.3631 0.07140 0.06659 0.0242 0.0080 1.0000 18.750 1.3556 0.07554 0.07082 0.0230 0.0078 1.0000 19.000 1.3504 0.07945 0.07483 0.0218 0.0077 1.0000 19.250 1.3420 0.08386 0.07933 0.0204 0.0076 1.0000