XFOIL Version 6.96 Calculated polar for: AH 93-K-130/15 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.3173 0.11644 0.11445 -0.0223 0.7872 0.0127 -11.250 -0.3179 0.11243 0.11044 -0.0236 0.7866 0.0127 -8.500 -0.6499 0.02779 0.02404 -0.0371 0.7805 0.0107 -8.250 -0.6373 0.02513 0.02103 -0.0353 0.7798 0.0110 -8.000 -0.6206 0.02311 0.01871 -0.0338 0.7790 0.0112 -7.750 -0.6013 0.02153 0.01687 -0.0326 0.7782 0.0116 -7.500 -0.5797 0.02030 0.01543 -0.0318 0.7773 0.0119 -7.250 -0.5559 0.01930 0.01427 -0.0313 0.7765 0.0123 -7.000 -0.5305 0.01865 0.01350 -0.0310 0.7754 0.0126 -6.750 -0.5092 0.01688 0.01148 -0.0301 0.7741 0.0133 -6.500 -0.4839 0.01626 0.01080 -0.0299 0.7729 0.0139 -6.250 -0.4576 0.01586 0.01036 -0.0297 0.7717 0.0144 -6.000 -0.4313 0.01542 0.00986 -0.0296 0.7705 0.0149 -5.750 -0.4051 0.01492 0.00929 -0.0293 0.7694 0.0156 -5.500 -0.3788 0.01443 0.00873 -0.0291 0.7685 0.0162 -5.250 -0.3522 0.01404 0.00827 -0.0289 0.7676 0.0168 -5.000 -0.3249 0.01379 0.00797 -0.0289 0.7668 0.0172 -4.750 -0.3019 0.01270 0.00678 -0.0280 0.7659 0.0189 -4.500 -0.2747 0.01249 0.00657 -0.0280 0.7651 0.0201 -4.250 -0.2476 0.01229 0.00634 -0.0279 0.7641 0.0215 -4.000 -0.2200 0.01208 0.00610 -0.0279 0.7628 0.0226 -3.750 -0.1925 0.01179 0.00579 -0.0280 0.7612 0.0235 -3.500 -0.1670 0.01123 0.00520 -0.0276 0.7596 0.0259 -3.250 -0.1394 0.01101 0.00499 -0.0277 0.7580 0.0277 -3.000 -0.1115 0.01083 0.00480 -0.0278 0.7566 0.0297 -2.750 -0.0834 0.01069 0.00465 -0.0279 0.7554 0.0309 -2.500 -0.0573 0.01026 0.00416 -0.0276 0.7543 0.0342 -2.250 -0.0297 0.01002 0.00393 -0.0276 0.7532 0.0377 -2.000 -0.0020 0.00983 0.00371 -0.0276 0.7521 0.0405 -1.750 0.0252 0.00957 0.00343 -0.0275 0.7510 0.0467 -1.500 0.0528 0.00941 0.00327 -0.0275 0.7496 0.0541 -1.250 0.0801 0.00913 0.00315 -0.0276 0.7476 0.0856 -1.000 0.1060 0.00873 0.00303 -0.0274 0.7455 0.1664 -0.750 0.1300 0.00816 0.00290 -0.0270 0.7435 0.2991 -0.500 0.1499 0.00731 0.00271 -0.0257 0.7415 0.5091 -0.250 0.1574 0.00609 0.00249 -0.0214 0.7396 0.7983 0.000 0.2231 0.00612 0.00292 -0.0292 0.7386 0.9404 0.250 0.2426 0.00623 0.00297 -0.0271 0.7369 0.9572 0.500 0.2892 0.00644 0.00315 -0.0312 0.7348 0.9633 0.750 0.3403 0.00675 0.00345 -0.0360 0.7323 0.9740 1.000 0.3965 0.00700 0.00368 -0.0420 0.7298 0.9843 1.250 0.4523 0.00691 0.00356 -0.0482 0.7273 0.9888 1.500 0.4883 0.00681 0.00343 -0.0501 0.7248 0.9917 1.750 0.5191 0.00678 0.00336 -0.0509 0.7221 0.9940 2.000 0.5546 0.00667 0.00328 -0.0529 0.7180 0.9948 2.250 0.5894 0.00655 0.00316 -0.0546 0.7140 0.9958 2.500 0.6231 0.00643 0.00301 -0.0561 0.7103 0.9969 2.750 0.6566 0.00637 0.00296 -0.0576 0.7051 0.9980 3.000 0.6898 0.00629 0.00289 -0.0591 0.6992 0.9991 3.250 0.7225 0.00622 0.00281 -0.0604 0.6923 1.0000 3.500 0.7499 0.00619 0.00275 -0.0605 0.6830 1.0000 3.750 0.7777 0.00619 0.00274 -0.0608 0.6727 1.0000 4.000 0.8056 0.00621 0.00275 -0.0611 0.6622 1.0000 4.250 0.8335 0.00627 0.00277 -0.0614 0.6490 1.0000 4.500 0.8616 0.00637 0.00282 -0.0619 0.6325 1.0000 5.000 0.9181 0.00672 0.00304 -0.0629 0.5919 1.0000 5.250 0.9463 0.00696 0.00320 -0.0635 0.5698 1.0000 5.500 0.9742 0.00723 0.00340 -0.0641 0.5456 1.0000 5.750 1.0019 0.00764 0.00368 -0.0648 0.5122 1.0000 6.000 1.0287 0.00812 0.00401 -0.0654 0.4746 1.0000 6.250 1.0541 0.00879 0.00446 -0.0659 0.4265 1.0000 6.500 1.0779 0.00944 0.00492 -0.0662 0.3843 1.0000 7.000 1.1164 0.01116 0.00615 -0.0653 0.2849 1.0000 7.250 1.1304 0.01217 0.00690 -0.0640 0.2364 1.0000 7.500 1.1413 0.01323 0.00775 -0.0623 0.1952 1.0000 7.750 1.1466 0.01428 0.00864 -0.0596 0.1620 1.0000 8.000 1.1405 0.01518 0.00942 -0.0543 0.1387 1.0000 8.250 1.1333 0.01595 0.01011 -0.0486 0.1199 1.0000 8.500 1.1318 0.01676 0.01082 -0.0441 0.1000 1.0000 8.750 1.1336 0.01756 0.01152 -0.0403 0.0829 1.0000 9.000 1.1385 0.01831 0.01220 -0.0371 0.0684 1.0000 9.250 1.1434 0.01909 0.01292 -0.0340 0.0554 1.0000 9.500 1.1493 0.01986 0.01364 -0.0310 0.0445 1.0000 9.750 1.1556 0.02065 0.01438 -0.0282 0.0359 1.0000 10.000 1.1628 0.02143 0.01513 -0.0256 0.0306 1.0000 10.250 1.1717 0.02216 0.01589 -0.0232 0.0267 1.0000 10.500 1.1811 0.02288 0.01662 -0.0210 0.0242 1.0000 10.750 1.1870 0.02384 0.01758 -0.0184 0.0211 1.0000 11.000 1.1975 0.02458 0.01837 -0.0165 0.0198 1.0000 11.250 1.2085 0.02531 0.01914 -0.0147 0.0187 1.0000 11.500 1.2180 0.02616 0.02002 -0.0128 0.0175 1.0000 11.750 1.2262 0.02715 0.02102 -0.0109 0.0162 1.0000 12.000 1.2289 0.02856 0.02251 -0.0084 0.0147 1.0000 12.250 1.2418 0.02934 0.02333 -0.0072 0.0143 1.0000 12.500 1.2538 0.03024 0.02427 -0.0059 0.0136 1.0000 12.750 1.2643 0.03130 0.02538 -0.0047 0.0129 1.0000 13.000 1.2745 0.03243 0.02654 -0.0035 0.0122 1.0000 13.250 1.2819 0.03382 0.02797 -0.0021 0.0115 1.0000 13.500 1.2799 0.03604 0.03030 -0.0001 0.0105 1.0000 13.750 1.2928 0.03709 0.03139 0.0006 0.0103 1.0000 14.000 1.3041 0.03829 0.03265 0.0014 0.0099 1.0000 14.250 1.3139 0.03966 0.03408 0.0022 0.0094 1.0000 14.500 1.3231 0.04110 0.03557 0.0030 0.0089 1.0000 14.750 1.3312 0.04269 0.03721 0.0037 0.0085 1.0000 15.000 1.3370 0.04452 0.03909 0.0045 0.0081 1.0000 15.250 1.3358 0.04711 0.04176 0.0055 0.0077 1.0000 15.500 1.3315 0.05006 0.04483 0.0066 0.0073 1.0000 15.750 1.3393 0.05186 0.04671 0.0070 0.0072 1.0000 16.000 1.3457 0.05385 0.04877 0.0073 0.0069 1.0000 16.250 1.3503 0.05607 0.05107 0.0076 0.0067 1.0000 16.500 1.3538 0.05844 0.05352 0.0079 0.0065 1.0000 16.750 1.3568 0.06090 0.05607 0.0081 0.0062 1.0000 17.000 1.3592 0.06350 0.05875 0.0081 0.0060 1.0000 17.250 1.3611 0.06621 0.06152 0.0081 0.0058 1.0000 17.500 1.3609 0.06923 0.06462 0.0079 0.0057 1.0000 17.750 1.3574 0.07269 0.06817 0.0076 0.0055 1.0000 18.000 1.3492 0.07685 0.07244 0.0072 0.0053 1.0000 18.250 1.3355 0.08187 0.07759 0.0066 0.0051 1.0000