XFOIL Version 6.96 Calculated polar for: Fage & Collins 1 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4235 0.08815 0.08645 -0.0309 0.9978 0.0121 -9.250 -0.4153 0.08361 0.08192 -0.0355 0.9962 0.0122 -9.000 -0.4256 0.07398 0.07228 -0.0463 0.9913 0.0135 -8.750 -0.4091 0.07004 0.06833 -0.0519 0.9879 0.0136 -8.250 -0.3786 0.06242 0.06065 -0.0610 0.9790 0.0138 -8.000 -0.3667 0.05914 0.05733 -0.0633 0.9702 0.0140 -7.750 -0.3576 0.05554 0.05368 -0.0649 0.9526 0.0142 -7.500 -0.3373 0.05083 0.04886 -0.0692 0.9434 0.0146 -7.250 -0.3154 0.03842 0.03598 -0.0770 0.9355 0.0163 -7.000 -0.2873 0.03503 0.03242 -0.0801 0.9317 0.0165 -6.750 -0.2548 0.03282 0.03008 -0.0831 0.9285 0.0167 -6.500 -0.2193 0.03042 0.02752 -0.0865 0.9246 0.0169 -6.250 -0.1797 0.02794 0.02485 -0.0907 0.9196 0.0172 -6.000 -0.1425 0.02565 0.02233 -0.0940 0.9128 0.0177 -5.750 -0.1166 0.02295 0.01935 -0.0944 0.9050 0.0183 -5.500 -0.0932 0.02033 0.01640 -0.0939 0.8980 0.0187 -5.250 -0.0746 0.01809 0.01386 -0.0921 0.8915 0.0190 -5.000 -0.0542 0.01610 0.01153 -0.0905 0.8855 0.0194 -4.750 -0.0322 0.01478 0.00992 -0.0892 0.8797 0.0197 -4.500 -0.0108 0.01376 0.00877 -0.0880 0.8735 0.0199 -4.250 0.0137 0.01316 0.00806 -0.0873 0.8671 0.0201 -4.000 0.0365 0.01257 0.00739 -0.0862 0.8598 0.0202 -3.750 0.0608 0.01210 0.00683 -0.0854 0.8525 0.0204 -3.500 0.0847 0.01169 0.00637 -0.0845 0.8452 0.0206 -3.250 0.1088 0.01127 0.00587 -0.0836 0.8359 0.0209 -3.000 0.1321 0.01080 0.00532 -0.0825 0.8235 0.0211 -2.750 0.1562 0.01039 0.00484 -0.0816 0.8130 0.0212 -2.500 0.1802 0.00999 0.00437 -0.0806 0.8011 0.0214 -2.250 0.2035 0.00965 0.00394 -0.0795 0.7843 0.0215 -2.000 0.2253 0.00939 0.00357 -0.0780 0.7605 0.0217 -1.750 0.2457 0.00920 0.00323 -0.0762 0.7287 0.0219 -1.500 0.2647 0.00917 0.00302 -0.0741 0.6860 0.0222 -1.250 0.2824 0.00915 0.00278 -0.0718 0.6344 0.0223 -1.000 0.3013 0.00913 0.00257 -0.0697 0.5887 0.0225 -0.750 0.3208 0.00912 0.00240 -0.0679 0.5470 0.0226 -0.500 0.3422 0.00909 0.00225 -0.0664 0.5187 0.0229 -0.250 0.3641 0.00909 0.00215 -0.0651 0.4939 0.0232 0.000 0.3865 0.00910 0.00207 -0.0639 0.4688 0.0234 0.250 0.4090 0.00912 0.00200 -0.0627 0.4464 0.0235 0.500 0.4309 0.00900 0.00182 -0.0614 0.4276 0.0241 0.750 0.4538 0.00899 0.00175 -0.0603 0.4087 0.0245 1.000 0.4766 0.00902 0.00172 -0.0592 0.3885 0.0249 1.250 0.4993 0.00908 0.00170 -0.0581 0.3674 0.0251 1.500 0.5225 0.00913 0.00170 -0.0570 0.3493 0.0255 1.750 0.5458 0.00920 0.00172 -0.0561 0.3318 0.0262 2.000 0.5690 0.00928 0.00175 -0.0551 0.3148 0.0269 2.250 0.5921 0.00937 0.00178 -0.0541 0.2975 0.0273 2.500 0.6151 0.00948 0.00183 -0.0530 0.2795 0.0278 2.750 0.6377 0.00962 0.00190 -0.0520 0.2596 0.0282 3.000 0.6603 0.00977 0.00197 -0.0509 0.2389 0.0291 3.250 0.6820 0.00999 0.00208 -0.0497 0.2130 0.0303 3.500 0.7038 0.01021 0.00221 -0.0485 0.1899 0.0319 3.750 0.7262 0.01040 0.00233 -0.0474 0.1755 0.0335 4.000 0.8925 0.00934 0.00324 -0.0806 0.1548 1.0000 4.250 0.9157 0.00946 0.00337 -0.0796 0.1518 1.0000 4.500 0.9386 0.00961 0.00351 -0.0786 0.1478 1.0000 4.750 0.9610 0.00979 0.00367 -0.0775 0.1427 1.0000 5.000 0.9836 0.00996 0.00383 -0.0765 0.1380 1.0000 5.250 1.0058 0.01015 0.00400 -0.0754 0.1299 1.0000 5.500 1.0278 0.01035 0.00418 -0.0743 0.1229 1.0000 5.750 1.0489 0.01062 0.00438 -0.0730 0.1092 1.0000 6.250 1.0872 0.01141 0.00496 -0.0698 0.0735 1.0000 6.500 1.1073 0.01174 0.00526 -0.0684 0.0643 1.0000 6.750 1.1276 0.01206 0.00555 -0.0670 0.0571 1.0000 7.000 1.1473 0.01241 0.00587 -0.0655 0.0501 1.0000 7.250 1.1676 0.01272 0.00617 -0.0642 0.0450 1.0000 7.500 1.1868 0.01308 0.00651 -0.0627 0.0389 1.0000 7.750 1.2053 0.01350 0.00689 -0.0610 0.0315 1.0000 8.250 1.2400 0.01449 0.00779 -0.0573 0.0174 1.0000 8.500 1.2582 0.01490 0.00821 -0.0557 0.0150 1.0000 8.750 1.2761 0.01532 0.00865 -0.0540 0.0135 1.0000 9.000 1.2933 0.01577 0.00913 -0.0521 0.0121 1.0000 9.250 1.3112 0.01616 0.00956 -0.0505 0.0116 1.0000 9.500 1.3281 0.01658 0.01002 -0.0486 0.0110 1.0000 9.750 1.3432 0.01699 0.01047 -0.0464 0.0104 1.0000 10.000 1.3564 0.01745 0.01096 -0.0439 0.0097 1.0000 10.250 1.3691 0.01796 0.01152 -0.0413 0.0091 1.0000 10.500 1.3820 0.01846 0.01207 -0.0388 0.0088 1.0000 10.750 1.3960 0.01892 0.01259 -0.0365 0.0086 1.0000 11.000 1.4099 0.01939 0.01312 -0.0343 0.0082 1.0000 11.250 1.4227 0.01995 0.01373 -0.0321 0.0080 1.0000 11.500 1.4353 0.02053 0.01438 -0.0298 0.0078 1.0000 11.750 1.4471 0.02117 0.01506 -0.0275 0.0073 1.0000 12.000 1.4589 0.02181 0.01576 -0.0253 0.0071 1.0000 12.250 1.4678 0.02266 0.01668 -0.0228 0.0068 1.0000 12.500 1.4758 0.02359 0.01768 -0.0202 0.0066 1.0000 12.750 1.4846 0.02447 0.01864 -0.0180 0.0064 1.0000 13.000 1.4949 0.02527 0.01951 -0.0160 0.0062 1.0000 13.250 1.5031 0.02624 0.02056 -0.0139 0.0061 1.0000 13.500 1.5113 0.02724 0.02164 -0.0120 0.0059 1.0000 13.750 1.5166 0.02849 0.02298 -0.0099 0.0059 1.0000 14.000 1.5221 0.02977 0.02436 -0.0080 0.0057 1.0000 14.250 1.5266 0.03117 0.02585 -0.0062 0.0056 1.0000 14.500 1.5310 0.03265 0.02740 -0.0045 0.0054 1.0000 14.750 1.5333 0.03437 0.02922 -0.0030 0.0054 1.0000 15.000 1.5349 0.03622 0.03116 -0.0016 0.0053 1.0000 15.250 1.5340 0.03843 0.03347 -0.0004 0.0052 1.0000 15.500 1.5320 0.04088 0.03603 0.0005 0.0052 1.0000 15.750 1.5287 0.04363 0.03888 0.0010 0.0050 1.0000 16.000 1.5213 0.04706 0.04242 0.0011 0.0048 1.0000 16.250 1.5138 0.05078 0.04627 0.0008 0.0048 1.0000 16.500 1.5037 0.05512 0.05073 -0.0002 0.0047 1.0000 16.750 1.4901 0.06036 0.05612 -0.0019 0.0047 1.0000 17.000 1.4747 0.06614 0.06205 -0.0042 0.0047 1.0000 17.250 1.4568 0.07253 0.06857 -0.0068 0.0047 1.0000 17.500 1.4335 0.08002 0.07622 -0.0101 0.0047 1.0000 17.750 1.4118 0.08734 0.08368 -0.0133 0.0047 1.0000 18.000 1.3813 0.09641 0.09291 -0.0174 0.0047 1.0000 18.250 1.3583 0.10427 0.10091 -0.0209 0.0048 1.0000 18.500 1.3262 0.11404 0.11082 -0.0254 0.0048 1.0000