XFOIL Version 6.96 Calculated polar for: TH 25816 HALE AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.3036 0.05818 0.05362 -0.2518 0.9407 0.0107 -19.500 -0.3047 0.05563 0.05101 -0.2524 0.9401 0.0108 -19.250 -0.3021 0.05336 0.04867 -0.2533 0.9393 0.0109 -19.000 -0.2962 0.05138 0.04664 -0.2541 0.9386 0.0110 -18.750 -0.2928 0.04933 0.04453 -0.2547 0.9380 0.0111 -18.500 -0.2866 0.04758 0.04273 -0.2552 0.9375 0.0111 -18.250 -0.2806 0.04583 0.04093 -0.2557 0.9368 0.0113 -18.000 -0.2719 0.04424 0.03928 -0.2563 0.9360 0.0113 -17.750 -0.2707 0.04285 0.03784 -0.2551 0.9350 0.0113 -17.500 -0.2719 0.04154 0.03650 -0.2532 0.9339 0.0114 -17.250 -0.2691 0.04042 0.03535 -0.2517 0.9323 0.0115 -17.000 -0.2653 0.03921 0.03410 -0.2505 0.9309 0.0116 -16.750 -0.2601 0.03798 0.03283 -0.2496 0.9297 0.0116 -16.500 -0.2510 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0.7257 3.250 0.5354 0.01073 0.00594 -0.0645 0.6443 0.7292 3.500 0.5567 0.01090 0.00613 -0.0638 0.6422 0.7327 3.750 0.5790 0.01106 0.00631 -0.0634 0.6397 0.7357 4.000 0.6009 0.01121 0.00649 -0.0630 0.6368 0.7388 4.250 0.6227 0.01137 0.00666 -0.0624 0.6338 0.7423 4.500 0.6445 0.01154 0.00683 -0.0619 0.6309 0.7458 4.750 0.6666 0.01171 0.00699 -0.0615 0.6277 0.7498 5.000 0.6870 0.01193 0.00724 -0.0608 0.6248 0.7534 5.250 0.7065 0.01216 0.00751 -0.0599 0.6214 0.7570 5.500 0.7255 0.01240 0.00778 -0.0589 0.6173 0.7610 5.750 0.7448 0.01265 0.00802 -0.0580 0.6133 0.7649 6.000 0.7650 0.01289 0.00827 -0.0573 0.6098 0.7686 6.250 0.7846 0.01316 0.00857 -0.0565 0.6060 0.7719 6.500 0.8013 0.01350 0.00894 -0.0551 0.6014 0.7754 6.750 0.8181 0.01384 0.00928 -0.0538 0.5965 0.7793 7.000 0.8365 0.01416 0.00962 -0.0528 0.5920 0.7833 7.250 0.8523 0.01457 0.01005 -0.0514 0.5859 0.7870 7.500 0.8656 0.01504 0.01052 -0.0495 0.5798 0.7903 7.750 0.8827 0.01542 0.01093 -0.0484 0.5745 0.7935 8.000 0.8977 0.01588 0.01142 -0.0469 0.5676 0.7969 8.250 0.9077 0.01651 0.01204 -0.0445 0.5597 0.8003 8.500 0.9207 0.01708 0.01260 -0.0428 0.5503 0.8034 8.750 0.9271 0.01789 0.01339 -0.0400 0.5384 0.8064 9.000 0.9338 0.01871 0.01419 -0.0372 0.5274 0.8094 9.250 0.9347 0.01979 0.01525 -0.0336 0.5117 0.8125 9.500 0.9382 0.02079 0.01622 -0.0305 0.4959 0.8157 9.750 0.9336 0.02220 0.01755 -0.0262 0.4751 0.8186 10.000 0.9261 0.02381 0.01906 -0.0217 0.4513 0.8212 10.250 0.9214 0.02534 0.02049 -0.0177 0.4298 0.8234 10.500 0.9206 0.02672 0.02184 -0.0144 0.4125 0.8259 10.750 0.9196 0.02816 0.02322 -0.0112 0.3941 0.8284 11.000 0.9185 0.02965 0.02465 -0.0081 0.3740 0.8308 11.250 0.9213 0.03100 0.02595 -0.0056 0.3581 0.8331 11.500 0.9229 0.03244 0.02732 -0.0031 0.3398 0.8351 11.750 0.9269 0.03380 0.02862 -0.0009 0.3234 0.8370 12.000 0.9309 0.03518 0.02995 0.0011 0.3084 0.8387 12.250 0.9376 0.03644 0.03114 0.0027 0.2930 0.8402 12.500 0.9409 0.03791 0.03257 0.0048 0.2767 0.8420 12.750 0.9471 0.03921 0.03383 0.0064 0.2621 0.8438 13.000 0.9553 0.04042 0.03502 0.0077 0.2493 0.8455 13.250 0.9607 0.04185 0.03641 0.0093 0.2365 0.8471 13.500 0.9679 0.04316 0.03768 0.0106 0.2241 0.8486 13.750 0.9732 0.04463 0.03909 0.0120 0.2084 0.8501 14.000 0.9807 0.04601 0.04044 0.0132 0.1970 0.8517 14.250 0.9897 0.04728 0.04169 0.0141 0.1866 0.8532 14.500 0.9966 0.04873 0.04308 0.0152 0.1737 0.8547 14.750 1.0027 0.05028 0.04460 0.0163 0.1631 0.8559 15.000 1.0114 0.05165 0.04592 0.0171 0.1524 0.8570 15.250 1.0171 0.05325 0.04746 0.0181 0.1387 0.8580 15.500 1.0242 0.05476 0.04896 0.0189 0.1310 0.8594 15.750 1.0325 0.05619 0.05038 0.0196 0.1225 0.8608 16.000 1.0407 0.05763 0.05181 0.0203 0.1139 0.8621 16.250 1.0465 0.05932 0.05348 0.0211 0.1062 0.8635 16.500 1.0565 0.06069 0.05487 0.0215 0.1011 0.8648 16.750 1.0648 0.06219 0.05636 0.0220 0.0954 0.8661 17.000 1.0720 0.06383 0.05801 0.0225 0.0886 0.8674 17.250 1.0798 0.06543 0.05961 0.0229 0.0842 0.8688 17.500 1.0892 0.06691 0.06109 0.0231 0.0803 0.8701 17.750 1.0978 0.06848 0.06268 0.0234 0.0762 0.8713 18.000 1.1047 0.07025 0.06446 0.0237 0.0728 0.8724 18.250 1.1139 0.07180 0.06603 0.0238 0.0696 0.8734 18.500 1.1227 0.07342 0.06767 0.0238 0.0664 0.8742 18.750 1.1280 0.07539 0.06964 0.0240 0.0628 0.8748 19.000 1.1361 0.07708 0.07136 0.0241 0.0597 0.8759 19.250 1.1449 0.07867 0.07300 0.0240 0.0579 0.8770