XFOIL Version 6.96 Calculated polar for: ULTIMATE 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.750 -0.7677 0.11815 0.11315 0.0041 1.0000 0.0278 -13.500 -0.8600 0.09141 0.08607 -0.0144 1.0000 0.0254 -13.250 -0.8956 0.08157 0.07596 -0.0210 1.0000 0.0251 -13.000 -0.9202 0.07473 0.06887 -0.0248 1.0000 0.0250 -12.750 -0.9407 0.06915 0.06303 -0.0270 1.0000 0.0249 -12.500 -0.9562 0.06463 0.05829 -0.0280 1.0000 0.0250 -12.250 -0.9694 0.06066 0.05408 -0.0281 1.0000 0.0251 -12.000 -0.9786 0.05735 0.05057 -0.0275 1.0000 0.0254 -11.750 -0.9853 0.05450 0.04752 -0.0263 1.0000 0.0257 -11.500 -0.9901 0.05195 0.04474 -0.0246 1.0000 0.0262 -11.250 -0.9924 0.04968 0.04228 -0.0226 1.0000 0.0269 -11.000 -0.9935 0.04752 0.03989 -0.0201 1.0000 0.0277 -10.750 -0.9931 0.04531 0.03741 -0.0174 1.0000 0.0284 -10.500 -0.9885 0.04307 0.03486 -0.0151 1.0000 0.0293 -10.250 -0.9788 0.04081 0.03227 -0.0132 1.0000 0.0300 -10.000 -0.9655 0.03871 0.02985 -0.0117 1.0000 0.0307 -9.750 -0.9489 0.03650 0.02749 -0.0106 1.0000 0.0316 -9.500 -0.9326 0.03474 0.02569 -0.0096 1.0000 0.0328 -9.250 -0.9170 0.03336 0.02422 -0.0083 1.0000 0.0346 -9.000 -0.9002 0.03203 0.02274 -0.0070 1.0000 0.0368 -8.750 -0.8821 0.03069 0.02122 -0.0058 1.0000 0.0386 -8.500 -0.8658 0.02921 0.01968 -0.0043 1.0000 0.0402 -8.250 -0.8520 0.02789 0.01836 -0.0025 1.0000 0.0424 -8.000 -0.8366 0.02684 0.01723 -0.0008 1.0000 0.0457 -7.750 -0.8206 0.02586 0.01611 0.0009 1.0000 0.0490 -7.500 -0.8080 0.02467 0.01491 0.0032 1.0000 0.0522 -7.250 -0.7931 0.02372 0.01389 0.0051 1.0000 0.0570 -7.000 -0.7786 0.02276 0.01289 0.0072 1.0000 0.0639 -6.750 -0.7635 0.02187 0.01195 0.0092 1.0000 0.0732 -6.500 -0.7506 0.02083 0.01104 0.0116 1.0000 0.0900 -6.250 -0.7393 0.01974 0.01023 0.0141 1.0000 0.1298 -6.000 -0.7288 0.01871 0.00957 0.0169 1.0000 0.1902 -5.750 -0.7182 0.01789 0.00909 0.0197 1.0000 0.2528 -5.500 -0.7057 0.01733 0.00876 0.0223 1.0000 0.3073 -5.250 -0.6917 0.01693 0.00847 0.0248 1.0000 0.3519 -5.000 -0.6771 0.01660 0.00823 0.0272 1.0000 0.3920 -4.750 -0.6637 0.01625 0.00805 0.0298 1.0000 0.4355 -4.500 -0.6493 0.01595 0.00790 0.0323 1.0000 0.4747 -4.250 -0.6315 0.01571 0.00773 0.0341 0.9996 0.5052 -4.000 -0.5950 0.01551 0.00754 0.0321 0.9937 0.5335 -3.750 -0.5585 0.01532 0.00736 0.0302 0.9869 0.5617 -3.500 -0.5219 0.01516 0.00721 0.0283 0.9799 0.5903 -3.250 -0.4835 0.01503 0.00711 0.0260 0.9735 0.6195 -3.000 -0.4488 0.01491 0.00702 0.0247 0.9651 0.6475 -2.750 -0.4128 0.01481 0.00692 0.0231 0.9574 0.6746 -2.500 -0.3793 0.01471 0.00682 0.0220 0.9482 0.6999 -2.250 -0.3462 0.01462 0.00675 0.0211 0.9385 0.7221 -2.000 -0.3115 0.01453 0.00663 0.0199 0.9301 0.7437 -1.750 -0.2786 0.01445 0.00656 0.0191 0.9198 0.7631 -1.500 -0.2448 0.01438 0.00650 0.0182 0.9098 0.7813 -1.250 -0.2092 0.01431 0.00641 0.0169 0.9010 0.7986 -1.000 -0.1764 0.01426 0.00637 0.0162 0.8897 0.8153 -0.750 -0.1434 0.01423 0.00633 0.0155 0.8784 0.8312 -0.500 -0.1099 0.01420 0.00628 0.0147 0.8671 0.8465 -0.250 -0.0762 0.01417 0.00624 0.0138 0.8554 0.8609 0.000 -0.0424 0.01416 0.00623 0.0129 0.8422 0.8747 0.250 -0.0082 0.01416 0.00624 0.0118 0.8279 0.8876 0.500 0.0266 0.01418 0.00626 0.0105 0.8131 0.9001 0.750 0.0645 0.01421 0.00631 0.0087 0.7976 0.9103 1.000 0.1036 0.01425 0.00636 0.0066 0.7818 0.9192 1.250 0.1407 0.01429 0.00640 0.0048 0.7656 0.9289 1.500 0.1812 0.01437 0.00649 0.0024 0.7485 0.9358 1.750 0.2180 0.01445 0.00658 0.0007 0.7310 0.9446 2.000 0.2558 0.01457 0.00671 -0.0012 0.7134 0.9533 2.250 0.2941 0.01470 0.00685 -0.0032 0.6958 0.9632 2.500 0.3312 0.01486 0.00700 -0.0051 0.6778 0.9750 3.000 0.4036 0.01517 0.00730 -0.0088 0.6355 0.9952 3.250 0.4376 0.01525 0.00737 -0.0103 0.6148 1.0000 3.500 0.4599 0.01528 0.00741 -0.0095 0.5973 1.0000 3.750 0.4825 0.01534 0.00749 -0.0087 0.5800 1.0000 4.000 0.5050 0.01542 0.00761 -0.0078 0.5618 1.0000 4.250 0.5267 0.01553 0.00768 -0.0067 0.5358 1.0000 4.500 0.5476 0.01567 0.00774 -0.0055 0.4946 1.0000 4.750 0.5679 0.01593 0.00779 -0.0042 0.4417 1.0000 5.000 0.5885 0.01629 0.00796 -0.0030 0.3826 1.0000 5.250 0.6081 0.01686 0.00821 -0.0019 0.3040 1.0000 5.500 0.6249 0.01798 0.00876 -0.0007 0.2018 1.0000 6.000 0.6575 0.02058 0.01050 0.0020 0.0751 1.0000 6.250 0.6753 0.02156 0.01143 0.0034 0.0634 1.0000 6.500 0.6936 0.02242 0.01237 0.0047 0.0562 1.0000 6.750 0.7097 0.02351 0.01347 0.0064 0.0521 1.0000 7.000 0.7274 0.02440 0.01449 0.0080 0.0485 1.0000 7.250 0.7441 0.02537 0.01549 0.0095 0.0447 1.0000 7.500 0.7583 0.02673 0.01679 0.0113 0.0421 1.0000 7.750 0.7763 0.02782 0.01803 0.0128 0.0404 1.0000 8.000 0.7945 0.02901 0.01933 0.0143 0.0384 1.0000 8.250 0.8123 0.03019 0.02058 0.0156 0.0362 1.0000 8.500 0.8295 0.03148 0.02187 0.0168 0.0342 1.0000 8.750 0.8477 0.03333 0.02373 0.0180 0.0329 1.0000 9.000 0.8664 0.03498 0.02562 0.0193 0.0320 1.0000 9.250 0.8837 0.03687 0.02780 0.0206 0.0311 1.0000 9.500 0.8987 0.03883 0.03003 0.0222 0.0301 1.0000 9.750 0.9115 0.04072 0.03215 0.0238 0.0289 1.0000 10.000 0.9227 0.04247 0.03406 0.0254 0.0277 1.0000 10.250 0.9323 0.04433 0.03606 0.0271 0.0268 1.0000 10.500 0.9397 0.04664 0.03852 0.0288 0.0262 1.0000 10.750 0.9433 0.04957 0.04162 0.0307 0.0258 1.0000 11.000 0.9388 0.05231 0.04470 0.0336 0.0256 1.0000 11.250 0.9285 0.05505 0.04775 0.0368 0.0255 1.0000 11.500 0.9137 0.05793 0.05089 0.0398 0.0254 1.0000 11.750 0.8980 0.06126 0.05446 0.0416 0.0253 1.0000 12.000 0.8809 0.06509 0.05852 0.0424 0.0253 1.0000 12.250 0.8626 0.06950 0.06314 0.0419 0.0253 1.0000 12.500 0.8425 0.07466 0.06850 0.0402 0.0254 1.0000 12.750 0.8219 0.08055 0.07453 0.0375 0.0254 1.0000 13.000 0.8008 0.08723 0.08136 0.0337 0.0256 1.0000 13.250 0.7794 0.09471 0.08896 0.0292 0.0257 1.0000