XFOIL Version 6.96 Calculated polar for: NACA 747A315 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.4768 0.11111 0.10779 -0.0314 1.0000 0.0609 -11.750 -0.4586 0.10915 0.10583 -0.0297 1.0000 0.0619 -11.500 -0.4485 0.10630 0.10299 -0.0301 1.0000 0.0631 -11.250 -0.4433 0.10271 0.09943 -0.0317 1.0000 0.0647 -11.000 -0.3692 0.08681 0.08379 -0.0474 0.9240 0.0727 -10.750 -0.3521 0.08662 0.08353 -0.0435 0.9047 0.0744 -10.500 -0.3524 0.08335 0.08023 -0.0434 0.8918 0.0759 -10.250 -0.3603 0.07877 0.07562 -0.0446 0.8820 0.0776 -10.000 -0.3777 0.07219 0.06904 -0.0482 0.8735 0.0792 -9.750 -0.4146 0.06362 0.06039 -0.0539 0.8673 0.0796 -9.500 -0.5519 0.06328 0.05961 -0.0568 0.8869 0.0741 -9.250 -0.5506 0.06128 0.05754 -0.0548 0.8732 0.0756 -9.000 -0.5544 0.05905 0.05517 -0.0525 0.8607 0.0777 -8.750 -0.5641 0.05656 0.05242 -0.0496 0.8495 0.0805 -8.000 -0.6001 0.03800 0.03155 -0.0359 0.8220 0.0502 -7.750 -0.5854 0.03445 0.02777 -0.0345 0.8138 0.0491 -7.500 -0.5696 0.03212 0.02506 -0.0327 0.8058 0.0492 -7.250 -0.5512 0.03023 0.02279 -0.0311 0.7982 0.0497 -7.000 -0.5301 0.02838 0.02060 -0.0298 0.7905 0.0500 -6.750 -0.5075 0.02677 0.01866 -0.0288 0.7842 0.0503 -6.500 -0.4822 0.02504 0.01668 -0.0283 0.7763 0.0509 -6.250 -0.4551 0.02318 0.01474 -0.0283 0.7704 0.0524 -6.000 -0.4289 0.02232 0.01385 -0.0281 0.7633 0.0548 -5.750 -0.4024 0.02146 0.01288 -0.0278 0.7567 0.0572 -5.500 -0.3757 0.02066 0.01190 -0.0274 0.7513 0.0592 -5.250 -0.3481 0.01949 0.01072 -0.0274 0.7442 0.0617 -5.000 -0.3236 0.01877 0.01003 -0.0269 0.7383 0.0659 -4.750 -0.2988 0.01829 0.00946 -0.0263 0.7326 0.0705 -4.500 -0.2766 0.01741 0.00865 -0.0254 0.7261 0.0757 -4.250 -0.2534 0.01698 0.00815 -0.0246 0.7210 0.0832 -4.000 -0.2327 0.01636 0.00759 -0.0234 0.7161 0.0942 -3.750 -0.2115 0.01580 0.00712 -0.0224 0.7102 0.1130 -3.500 -0.1972 0.01469 0.00655 -0.0204 0.7055 0.2030 -3.250 -0.2018 0.01265 0.00605 -0.0152 0.7019 0.5274 -3.000 -0.1852 0.01280 0.00718 -0.0111 0.6969 0.7682 -2.750 -0.1605 0.01346 0.00779 -0.0092 0.6921 0.8068 -2.500 -0.1355 0.01408 0.00829 -0.0074 0.6882 0.8304 -2.250 -0.1062 0.01477 0.00885 -0.0062 0.6850 0.8473 -2.000 -0.0682 0.01558 0.00962 -0.0067 0.6803 0.8608 -1.750 -0.0159 0.01665 0.01059 -0.0093 0.6759 0.8789 -1.500 0.0809 0.01788 0.01164 -0.0200 0.6725 0.9004 -1.250 0.1331 0.01803 0.01164 -0.0244 0.6696 0.9075 -1.000 0.1579 0.01807 0.01162 -0.0241 0.6665 0.9156 -0.750 0.1978 0.01802 0.01154 -0.0268 0.6626 0.9191 -0.500 0.2295 0.01799 0.01146 -0.0280 0.6592 0.9237 -0.250 0.2488 0.01799 0.01142 -0.0267 0.6563 0.9301 0.000 0.2910 0.01787 0.01122 -0.0297 0.6538 0.9335 0.250 0.3268 0.01787 0.01113 -0.0315 0.6513 0.9388 0.500 0.3506 0.01796 0.01128 -0.0313 0.6478 0.9451 0.750 0.3883 0.01789 0.01121 -0.0338 0.6448 0.9480 1.000 0.4204 0.01787 0.01119 -0.0352 0.6420 0.9514 1.250 0.4469 0.01789 0.01120 -0.0354 0.6397 0.9550 1.500 0.4683 0.01795 0.01124 -0.0345 0.6374 0.9586 1.750 0.5023 0.01788 0.01113 -0.0362 0.6353 0.9605 2.000 0.5326 0.01798 0.01132 -0.0375 0.6324 0.9626 2.250 0.5614 0.01809 0.01150 -0.0384 0.6293 0.9652 2.500 0.5871 0.01817 0.01162 -0.0386 0.6261 0.9676 2.750 0.6109 0.01824 0.01171 -0.0382 0.6234 0.9700 3.000 0.6373 0.01826 0.01173 -0.0384 0.6210 0.9722 3.250 0.6678 0.01827 0.01173 -0.0393 0.6188 0.9736 3.500 0.6954 0.01852 0.01214 -0.0402 0.6148 0.9754 3.750 0.7234 0.01868 0.01239 -0.0410 0.6112 0.9776 4.000 0.7497 0.01875 0.01252 -0.0411 0.6079 0.9795 4.250 0.7755 0.01876 0.01255 -0.0411 0.6051 0.9812 4.500 0.8011 0.01880 0.01258 -0.0408 0.6025 0.9832 4.750 0.8281 0.01897 0.01294 -0.0416 0.5957 0.9850 5.000 0.8574 0.01863 0.01262 -0.0419 0.5899 0.9863 5.250 0.8868 0.01838 0.01239 -0.0422 0.5844 0.9878 5.500 0.9151 0.01795 0.01201 -0.0423 0.5744 0.9899 5.750 0.9419 0.01742 0.01149 -0.0420 0.5633 0.9917 6.000 0.9701 0.01681 0.01079 -0.0416 0.5535 0.9931 6.250 0.9965 0.01638 0.01044 -0.0415 0.5404 0.9947 6.500 1.0253 0.01607 0.01022 -0.0419 0.5276 0.9968 6.750 1.0537 0.01579 0.01004 -0.0422 0.5143 0.9988 7.000 1.0783 0.01559 0.00991 -0.0419 0.4993 1.0000 7.250 1.0960 0.01548 0.00988 -0.0402 0.4807 1.0000 7.500 1.1117 0.01545 0.00990 -0.0382 0.4551 1.0000 7.750 1.1221 0.01560 0.00998 -0.0354 0.3975 1.0000 8.000 1.1130 0.01673 0.01054 -0.0300 0.3149 1.0000 8.250 1.0938 0.01814 0.01159 -0.0231 0.2555 1.0000 8.500 1.0694 0.01922 0.01247 -0.0153 0.2199 1.0000 8.750 1.0386 0.01968 0.01291 -0.0059 0.2088 1.0000 9.000 1.0074 0.02008 0.01331 0.0031 0.2031 1.0000 9.250 0.9826 0.02143 0.01448 0.0096 0.1757 1.0000 9.500 0.9647 0.02373 0.01649 0.0133 0.1343 1.0000 9.750 0.9495 0.02640 0.01886 0.0161 0.1004 1.0000 10.000 0.9410 0.02887 0.02118 0.0181 0.0806 1.0000 10.250 0.9386 0.03104 0.02329 0.0196 0.0702 1.0000 10.500 0.9367 0.03323 0.02544 0.0209 0.0630 1.0000 10.750 0.9392 0.03514 0.02735 0.0219 0.0582 1.0000 11.000 0.9400 0.03720 0.02941 0.0231 0.0545 1.0000 11.250 0.9469 0.03882 0.03107 0.0238 0.0509 1.0000 11.500 0.9512 0.04065 0.03286 0.0247 0.0482 1.0000 11.750 0.9580 0.04230 0.03452 0.0257 0.0457 1.0000 12.000 0.9686 0.04369 0.03596 0.0265 0.0438 1.0000 12.250 0.9803 0.04499 0.03728 0.0273 0.0422 1.0000 12.500 0.9940 0.04615 0.03839 0.0282 0.0407 1.0000 12.750 1.0149 0.04693 0.03914 0.0294 0.0390 1.0000 13.000 1.0288 0.04825 0.04059 0.0299 0.0376 1.0000 13.250 1.0456 0.04943 0.04184 0.0306 0.0364 1.0000 13.500 1.0623 0.05070 0.04318 0.0311 0.0353 1.0000 13.750 1.0818 0.05192 0.04443 0.0317 0.0343 1.0000 14.000 1.1122 0.05308 0.04560 0.0323 0.0335 1.0000 14.250 1.1384 0.05522 0.04789 0.0328 0.0330 1.0000 14.500 1.1454 0.05764 0.05055 0.0332 0.0328 1.0000 14.750 1.1480 0.06046 0.05361 0.0336 0.0327 1.0000 15.000 1.1458 0.06360 0.05701 0.0339 0.0325 1.0000 15.250 1.1427 0.06699 0.06063 0.0340 0.0324 1.0000 15.500 1.1348 0.07066 0.06454 0.0339 0.0323 1.0000 15.750 1.1249 0.07470 0.06882 0.0335 0.0323 1.0000 16.000 1.1119 0.07917 0.07352 0.0327 0.0322 1.0000 16.250 1.0958 0.08409 0.07867 0.0315 0.0322 1.0000 16.500 1.0803 0.08932 0.08411 0.0300 0.0323 1.0000 16.750 1.0619 0.09506 0.09006 0.0279 0.0323 1.0000 17.000 1.0416 0.10141 0.09662 0.0252 0.0324 1.0000 17.250 1.0230 0.10810 0.10348 0.0224 0.0327 1.0000 17.500 1.0055 0.11496 0.11048 0.0192 0.0329 1.0000 17.750 0.9910 0.12148 0.11716 0.0159 0.0333 1.0000