XFOIL Version 6.96 Calculated polar for: AH 83-150 Q 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.2271 0.08413 0.08124 -0.0625 0.6833 0.0083 -9.250 -0.2271 0.08005 0.07718 -0.0648 0.6818 0.0081 -9.000 -0.2294 0.07564 0.07280 -0.0675 0.6802 0.0085 -8.750 -0.2344 0.07077 0.06796 -0.0710 0.6784 0.0085 -8.500 -0.2516 0.06429 0.06148 -0.0767 0.6767 0.0089 -8.250 -0.2655 0.06040 0.05755 -0.0779 0.6748 0.0084 -8.000 -0.2812 0.05662 0.05370 -0.0775 0.6729 0.0086 -7.750 -0.2855 0.05280 0.04977 -0.0775 0.6710 0.0087 -7.500 -0.2864 0.04874 0.04558 -0.0771 0.6692 0.0090 -7.250 -0.3039 0.03800 0.03431 -0.0742 0.6682 0.0100 -7.000 -0.2922 0.03579 0.03200 -0.0735 0.6667 0.0101 -6.750 -0.2776 0.03405 0.03015 -0.0730 0.6650 0.0103 -6.500 -0.2611 0.03233 0.02832 -0.0725 0.6632 0.0105 -6.250 -0.2433 0.03052 0.02636 -0.0720 0.6615 0.0108 -6.000 -0.2249 0.02827 0.02390 -0.0712 0.6599 0.0113 -5.750 -0.2019 0.02635 0.02155 -0.0696 0.6583 0.0127 -5.500 -0.1869 0.02253 0.01731 -0.0683 0.6565 0.0132 -5.250 -0.1630 0.02123 0.01594 -0.0683 0.6543 0.0135 -5.000 -0.1380 0.02029 0.01495 -0.0683 0.6530 0.0140 -4.750 -0.1124 0.01923 0.01377 -0.0682 0.6516 0.0148 -4.500 -0.0869 0.01784 0.01201 -0.0676 0.6500 0.0169 -4.250 -0.0601 0.01685 0.01104 -0.0677 0.6482 0.0175 -4.000 -0.0329 0.01612 0.01023 -0.0677 0.6464 0.0186 -3.250 0.0502 0.01189 0.00545 -0.0658 0.6416 0.0101 -3.000 0.0781 0.01167 0.00519 -0.0658 0.6395 0.0099 -2.750 0.1044 0.01101 0.00452 -0.0656 0.6377 0.0097 -2.500 0.1313 0.01051 0.00401 -0.0656 0.6363 0.0096 -2.000 0.1862 0.00967 0.00313 -0.0656 0.6326 0.0103 -1.750 0.2143 0.00940 0.00285 -0.0658 0.6306 0.0114 -1.500 0.2429 0.00923 0.00265 -0.0660 0.6286 0.0127 -1.250 0.2713 0.00904 0.00243 -0.0662 0.6266 0.0148 -1.000 0.2992 0.00877 0.00228 -0.0664 0.6241 0.0598 -0.750 0.3193 0.00663 0.00197 -0.0667 0.6222 0.6288 -0.500 0.3452 0.00646 0.00226 -0.0662 0.6203 0.7859 -0.250 0.3730 0.00675 0.00258 -0.0658 0.6180 0.8099 0.000 0.4000 0.00706 0.00291 -0.0652 0.6157 0.8235 0.250 0.4268 0.00732 0.00317 -0.0647 0.6134 0.8341 0.500 0.4540 0.00750 0.00334 -0.0643 0.6112 0.8399 0.750 0.4830 0.00767 0.00344 -0.0646 0.6084 0.8442 1.000 0.5118 0.00765 0.00343 -0.0649 0.6063 0.8466 1.250 0.5405 0.00762 0.00340 -0.0651 0.6036 0.8480 1.500 0.5697 0.00759 0.00336 -0.0655 0.6007 0.8488 1.750 0.5989 0.00758 0.00333 -0.0660 0.5978 0.8496 2.000 0.6279 0.00760 0.00331 -0.0664 0.5949 0.8506 2.250 0.6570 0.00763 0.00332 -0.0668 0.5920 0.8515 2.500 0.6864 0.00761 0.00332 -0.0673 0.5889 0.8523 2.750 0.7157 0.00760 0.00331 -0.0678 0.5856 0.8531 3.000 0.7448 0.00761 0.00330 -0.0683 0.5822 0.8540 3.250 0.7736 0.00767 0.00332 -0.0687 0.5784 0.8550 3.500 0.8029 0.00766 0.00335 -0.0692 0.5750 0.8559 3.750 0.8321 0.00766 0.00336 -0.0698 0.5709 0.8567 4.000 0.8611 0.00769 0.00338 -0.0702 0.5666 0.8575 4.250 0.8899 0.00773 0.00342 -0.0707 0.5618 0.8582 4.500 0.9188 0.00775 0.00344 -0.0712 0.5546 0.8589 4.750 0.9471 0.00781 0.00348 -0.0716 0.5468 0.8596 5.000 0.9755 0.00786 0.00353 -0.0720 0.5380 0.8603 5.250 1.0034 0.00789 0.00356 -0.0723 0.5309 0.8610 5.500 1.0310 0.00795 0.00362 -0.0725 0.5223 0.8617 5.750 1.0585 0.00802 0.00371 -0.0728 0.5131 0.8624 6.000 1.0854 0.00814 0.00381 -0.0730 0.5036 0.8630 6.250 1.1121 0.00828 0.00393 -0.0731 0.4921 0.8637 6.500 1.1381 0.00845 0.00409 -0.0731 0.4783 0.8645 6.750 1.1635 0.00866 0.00427 -0.0731 0.4637 0.8654 7.000 1.1882 0.00890 0.00447 -0.0729 0.4480 0.8663 7.250 1.2117 0.00921 0.00472 -0.0726 0.4301 0.8671 7.500 1.2345 0.00954 0.00500 -0.0722 0.4099 0.8679 7.750 1.2538 0.01005 0.00538 -0.0712 0.3826 0.8689 8.000 1.2708 0.01064 0.00583 -0.0699 0.3515 0.8699 8.500 1.3040 0.01170 0.00671 -0.0672 0.3057 0.8719 8.750 1.3184 0.01224 0.00717 -0.0655 0.2863 0.8730 9.000 1.3266 0.01282 0.00768 -0.0626 0.2682 0.8740 9.500 1.3336 0.01434 0.00909 -0.0560 0.2330 0.8768 9.750 1.3361 0.01539 0.01007 -0.0532 0.2146 0.8783 10.000 1.3380 0.01663 0.01124 -0.0506 0.1963 0.8797 10.250 1.3390 0.01806 0.01259 -0.0482 0.1777 0.8812 10.500 1.3436 0.01938 0.01387 -0.0463 0.1633 0.8827 10.750 1.3474 0.02081 0.01525 -0.0445 0.1486 0.8843 11.000 1.3519 0.02224 0.01663 -0.0429 0.1359 0.8856 11.250 1.3574 0.02366 0.01801 -0.0414 0.1250 0.8867 11.500 1.3678 0.02479 0.01916 -0.0404 0.1190 0.8876 11.750 1.3735 0.02626 0.02060 -0.0391 0.1099 0.8885 12.000 1.3804 0.02765 0.02198 -0.0380 0.1010 0.8898 12.250 1.3878 0.02903 0.02337 -0.0369 0.0935 0.8911 12.500 1.3930 0.03059 0.02490 -0.0358 0.0849 0.8924 12.750 1.3983 0.03219 0.02649 -0.0347 0.0762 0.8937 13.000 1.4029 0.03390 0.02819 -0.0337 0.0669 0.8949 13.250 1.4071 0.03572 0.02999 -0.0328 0.0587 0.8962 13.500 1.4108 0.03764 0.03189 -0.0320 0.0515 0.8977 13.750 1.4166 0.03944 0.03369 -0.0313 0.0468 0.8993 14.000 1.4218 0.04136 0.03563 -0.0307 0.0421 0.9006 14.250 1.4279 0.04323 0.03752 -0.0303 0.0387 0.9018 14.500 1.4320 0.04535 0.03966 -0.0298 0.0351 0.9031 14.750 1.4412 0.04700 0.04138 -0.0296 0.0338 0.9049 15.000 1.4474 0.04897 0.04340 -0.0293 0.0317 0.9067 15.250 1.4517 0.05116 0.04562 -0.0290 0.0292 0.9086 15.500 1.4583 0.05319 0.04772 -0.0289 0.0276 0.9106 15.750 1.4658 0.05515 0.04974 -0.0289 0.0263 0.9128 16.000 1.4708 0.05743 0.05208 -0.0289 0.0246 0.9153 16.250 1.4736 0.05995 0.05464 -0.0289 0.0224 0.9183 16.500 1.4802 0.06208 0.05687 -0.0290 0.0212 0.9233 16.750 1.4833 0.06463 0.05947 -0.0292 0.0187 0.9299 17.000 1.4863 0.06772 0.06264 -0.0301 0.0148 0.9483 17.250 1.4833 0.07154 0.06646 -0.0312 0.0096 1.0000 17.500 1.4785 0.07539 0.07034 -0.0318 0.0067 1.0000 17.750 1.4751 0.07917 0.07418 -0.0325 0.0055 1.0000 18.000 1.4712 0.08310 0.07818 -0.0334 0.0048 1.0000 18.250 1.4678 0.08703 0.08219 -0.0344 0.0042 1.0000 18.500 1.4660 0.09078 0.08605 -0.0355 0.0039 1.0000 18.750 1.4622 0.09490 0.09027 -0.0367 0.0037 1.0000 19.000 1.4605 0.09878 0.09423 -0.0380 0.0037 1.0000 19.250 1.4521 0.10376 0.09932 -0.0397 0.0033 1.0000