XFOIL Version 6.96 Calculated polar for: GOE 514 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 ------ -------- --------- --------- -------- -------- -------- -16.250 -0.4087 0.08597 0.08322 -0.1200 0.9730 0.0085 -16.000 -0.4182 0.08125 0.07845 -0.1225 0.9697 0.0086 -15.750 -0.4303 0.07595 0.07309 -0.1257 0.9667 0.0085 -15.500 -0.4432 0.07010 0.06718 -0.1301 0.9642 0.0086 -15.250 -0.4565 0.06385 0.06084 -0.1356 0.9619 0.0085 -15.000 -0.4809 0.05620 0.05308 -0.1426 0.9581 0.0086 -14.750 -0.6368 0.03199 0.02827 -0.1649 0.9380 0.0082 -14.500 -0.6343 0.02762 0.02366 -0.1674 0.9325 0.0082 -14.250 -0.6213 0.02479 0.02066 -0.1684 0.9285 0.0084 -14.000 -0.6064 0.02294 0.01869 -0.1682 0.9246 0.0085 -13.750 -0.5919 0.02171 0.01734 -0.1672 0.9205 0.0086 -13.500 -0.5751 0.02068 0.01620 -0.1663 0.9168 0.0088 -13.250 -0.5576 0.01980 0.01522 -0.1654 0.9133 0.0089 -13.000 -0.5499 0.01912 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0.01147 0.00390 -0.0445 0.3500 0.1850 2.000 0.5406 0.01153 0.00400 -0.0431 0.3468 0.1946 2.250 0.5608 0.01160 0.00410 -0.0417 0.3438 0.2071 2.500 0.5802 0.01169 0.00424 -0.0402 0.3395 0.2292 2.750 0.6002 0.01182 0.00436 -0.0388 0.3362 0.2373 3.000 0.6203 0.01194 0.00450 -0.0374 0.3333 0.2467 3.250 0.6412 0.01205 0.00463 -0.0362 0.3311 0.2529 3.500 0.6620 0.01217 0.00477 -0.0349 0.3285 0.2601 3.750 0.6827 0.01231 0.00490 -0.0337 0.3257 0.2651 4.000 0.7030 0.01246 0.00506 -0.0324 0.3228 0.2703 4.250 0.7227 0.01263 0.00523 -0.0311 0.3198 0.2747 4.500 0.7423 0.01281 0.00541 -0.0297 0.3168 0.2802 4.750 0.7633 0.01296 0.00557 -0.0287 0.3150 0.2844 5.000 0.7839 0.01311 0.00575 -0.0275 0.3122 0.2891 5.250 0.8045 0.01327 0.00593 -0.0264 0.3096 0.2940 5.500 0.8243 0.01348 0.00612 -0.0252 0.3064 0.2984 5.750 0.8426 0.01372 0.00636 -0.0238 0.3026 0.3021 6.000 0.8624 0.01392 0.00658 -0.0226 0.2998 0.3071 6.250 0.8832 0.01410 0.00679 -0.0216 0.2982 0.3112 6.500 0.9033 0.01431 0.00701 -0.0206 0.2942 0.3157 6.750 0.9229 0.01454 0.00725 -0.0194 0.2909 0.3203 7.000 0.9421 0.01479 0.00752 -0.0183 0.2888 0.3263 7.250 0.9603 0.01508 0.00782 -0.0170 0.2856 0.3331 7.500 0.9806 0.01530 0.00808 -0.0161 0.2836 0.3411 7.750 1.0011 0.01553 0.00835 -0.0152 0.2823 0.3511 8.000 1.0214 0.01576 0.00864 -0.0143 0.2797 0.3666 8.250 1.0408 0.01603 0.00896 -0.0134 0.2773 0.3829 8.500 1.0596 0.01634 0.00933 -0.0125 0.2734 0.4178 9.000 1.3066 0.01674 0.01114 -0.0563 0.2641 0.9990 9.250 1.3401 0.01719 0.01159 -0.0585 0.2603 1.0000 9.500 1.3527 0.01771 0.01207 -0.0565 0.2533 1.0000 9.750 1.3694 0.01807 0.01245 -0.0551 0.2502 1.0000 10.000 1.3827 0.01859 0.01295 -0.0532 0.2434 1.0000 10.250 1.3959 0.01915 0.01348 -0.0514 0.2381 1.0000 10.500 1.4115 0.01959 0.01395 -0.0500 0.2339 1.0000 10.750 1.4253 0.02015 0.01451 -0.0484 0.2293 1.0000 11.000 1.4373 0.02082 0.01516 -0.0466 0.2237 1.0000 11.250 1.4470 0.02163 0.01592 -0.0445 0.2119 1.0000 11.500 1.4597 0.02230 0.01661 -0.0430 0.2081 1.0000 11.750 1.4666 0.02333 0.01757 -0.0407 0.1956 1.0000 12.000 1.4687 0.02467 0.01882 -0.0381 0.1786 1.0000 12.250 1.4702 0.02611 0.02019 -0.0355 0.1636 1.0000 12.500 1.4704 0.02770 0.02172 -0.0329 0.1490 1.0000 12.750 1.4680 0.02954 0.02349 -0.0303 0.1344 1.0000 13.000 1.4680 0.03131 0.02522 -0.0281 0.1238 1.0000 13.250 1.4678 0.03316 0.02705 -0.0260 0.1148 1.0000 13.500 1.4674 0.03512 0.02899 -0.0241 0.1068 1.0000 13.750 1.4696 0.03694 0.03082 -0.0226 0.1005 1.0000 14.000 1.4653 0.03935 0.03320 -0.0208 0.0916 1.0000 14.250 1.4594 0.04200 0.03584 -0.0191 0.0806 1.0000 14.500 1.4288 0.04705 0.04079 -0.0164 0.0558 1.0000 14.750 1.4016 0.05212 0.04586 -0.0145 0.0391 1.0000 15.000 1.3745 0.05750 0.05126 -0.0131 0.0221 1.0000 15.250 1.3599 0.06178 0.05559 -0.0125 0.0163 1.0000 15.500 1.3527 0.06532 0.05921 -0.0121 0.0144 1.0000 15.750 1.3485 0.06862 0.06259 -0.0119 0.0137 1.0000 16.000 1.3428 0.07216 0.06621 -0.0119 0.0130 1.0000 16.250 1.3348 0.07606 0.07019 -0.0120 0.0122 1.0000 16.500 1.3280 0.07985 0.07406 -0.0121 0.0115 1.0000 16.750 1.3215 0.08365 0.07794 -0.0124 0.0112 1.0000 17.000 1.3151 0.08749 0.08186 -0.0128 0.0110 1.0000 17.250 1.3070 0.09160 0.08605 -0.0133 0.0105 1.0000 17.500 1.2978 0.09586 0.09039 -0.0138 0.0100 1.0000