AH 93-W-480B (ah93w480b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-480B (ah93w480b-il) Reynolds number: 50,000 Max Cl/Cd: 11.15 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w480b-il-50000-n5.txt Download as CSV file: xf-ah93w480b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-480B
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.3014 0.11866 0.10467 0.0348 0.9990 0.3027
-14.750 -1.2944 0.11752 0.10358 0.0369 0.9990 0.3045
-14.500 -1.2916 0.11645 0.10256 0.0399 0.9990 0.3073
-14.250 -1.3263 0.11326 0.09928 0.0498 0.9990 0.3106
-14.000 -1.3675 0.10953 0.09538 0.0611 0.9990 0.3142
-13.750 -1.4025 0.10584 0.09142 0.0715 0.9990 0.3184
-13.500 -1.4307 0.10247 0.08772 0.0808 0.9990 0.3221
-13.250 -1.4087 0.10280 0.08822 0.0808 0.9990 0.3247
-13.000 -1.3947 0.10273 0.08824 0.0823 0.9990 0.3275
-12.750 -1.3866 0.10233 0.08787 0.0849 0.9990 0.3308
-12.500 -1.3834 0.10158 0.08708 0.0885 0.9990 0.3347
-12.250 -1.3848 0.10041 0.08575 0.0929 0.9990 0.3390
-12.000 -1.3880 0.09905 0.08413 0.0978 0.9990 0.3432
-11.750 -1.3725 0.09920 0.08439 0.0988 0.9990 0.3461
-11.500 -1.3461 0.09931 0.08461 0.0974 0.9988 0.3497
-11.250 -1.3102 0.09905 0.08434 0.0937 0.9988 0.3547
-11.000 -1.2782 0.09785 0.08302 0.0906 0.9985 0.3598
-10.750 -1.2513 0.09641 0.08125 0.0887 0.9945 0.3663
-10.500 -1.2102 0.09627 0.08127 0.0838 0.9908 0.3700
-10.250 -1.1723 0.09582 0.08088 0.0797 0.9869 0.3747
-10.000 -1.1377 0.09494 0.07996 0.0762 0.9821 0.3807
-9.750 -1.1083 0.09377 0.07862 0.0737 0.9768 0.3864
-9.500 -1.0765 0.09274 0.07753 0.0708 0.9709 0.3919
-9.250 -1.0406 0.09217 0.07709 0.0671 0.9645 0.3966
-9.000 -1.0058 0.09145 0.07637 0.0636 0.9581 0.4021
-8.750 -0.9733 0.09049 0.07533 0.0606 0.9509 0.4083
-8.500 -0.9398 0.08956 0.07427 0.0574 0.9445 0.4152
-8.250 -0.9000 0.08917 0.07401 0.0530 0.9386 0.4213
-8.000 -0.8623 0.08857 0.07343 0.0489 0.9328 0.4279
-7.750 -0.8253 0.08773 0.07246 0.0449 0.9270 0.4354
-7.500 -0.7850 0.08709 0.07183 0.0403 0.9222 0.4423
-7.250 -0.7476 0.08665 0.07148 0.0364 0.9154 0.4490
-7.000 -0.7122 0.08611 0.07090 0.0329 0.9086 0.4566
-6.750 -0.6704 0.08523 0.06995 0.0279 0.9048 0.4657
-6.500 -0.6345 0.08493 0.06976 0.0245 0.8969 0.4726
-6.250 -0.5980 0.08447 0.06929 0.0208 0.8902 0.4809
-6.000 -0.5571 0.08360 0.06832 0.0161 0.8851 0.4905
-5.750 -0.5220 0.08350 0.06835 0.0128 0.8780 0.4979
-5.500 -0.4791 0.08268 0.06753 0.0077 0.8729 0.5091
-5.250 -0.4446 0.08237 0.06721 0.0045 0.8654 0.5183
-5.000 -0.4031 0.08189 0.06681 -0.0003 0.8601 0.5277
-4.750 -0.3545 0.08075 0.06558 -0.0068 0.8571 0.5409
-4.500 -0.3254 0.08113 0.06609 -0.0086 0.8464 0.5498
-4.250 -0.2760 0.08021 0.06516 -0.0153 0.8430 0.5627
-4.000 -0.2457 0.08044 0.06543 -0.0175 0.8331 0.5740
-3.750 -0.2005 0.07987 0.06491 -0.0232 0.8282 0.5872
-3.500 -0.1476 0.07884 0.06391 -0.0307 0.8252 0.6029
-3.250 -0.1245 0.07961 0.06473 -0.0311 0.8139 0.6149
-3.000 -0.0767 0.07895 0.06412 -0.0374 0.8094 0.6312
-2.750 -0.0258 0.07794 0.06309 -0.0444 0.8062 0.6496
-2.500 -0.0061 0.07916 0.06447 -0.0440 0.7944 0.6631
-2.250 0.0399 0.07846 0.06379 -0.0498 0.7894 0.6828
-2.000 0.0926 0.07742 0.06275 -0.0572 0.7861 0.7032
-1.750 0.1084 0.07892 0.06442 -0.0557 0.7735 0.7206
-1.500 0.1561 0.07838 0.06392 -0.0619 0.7686 0.7423
-1.250 0.2116 0.07748 0.06305 -0.0700 0.7651 0.7675
-1.000 0.2256 0.07940 0.06511 -0.0683 0.7530 0.7886
-0.750 0.2806 0.07933 0.06512 -0.0765 0.7476 0.8152
-0.500 0.3505 0.07909 0.06494 -0.0885 0.7439 0.8406
-0.250 0.3879 0.08146 0.06747 -0.0929 0.7335 0.8616
0.000 0.4564 0.08255 0.06861 -0.1049 0.7268 0.8811
0.250 0.5351 0.08294 0.06897 -0.1192 0.7224 0.8978
0.500 0.5913 0.08438 0.07042 -0.1281 0.7152 0.9120
0.750 0.6363 0.08620 0.07227 -0.1342 0.7056 0.9250
1.000 0.7001 0.08665 0.07265 -0.1448 0.7010 0.9374
1.250 0.7714 0.08631 0.07216 -0.1571 0.6970 0.9513
1.500 0.7913 0.09133 0.07713 -0.1583 0.6891 0.9964
1.750 0.8436 0.09297 0.07872 -0.1667 0.6823 1.0008
2.000 0.8686 0.09202 0.07759 -0.1684 0.6776 1.0010
2.250 0.9028 0.09057 0.07591 -0.1719 0.6739 1.0010
2.500 0.8828 0.09320 0.07858 -0.1628 0.6633 1.0010
2.750 0.9017 0.09336 0.07862 -0.1626 0.6572 1.0010
3.000 0.9376 0.09246 0.07756 -0.1662 0.6530 1.0010
3.250 0.9773 0.09148 0.07638 -0.1707 0.6494 1.0010
3.500 0.9311 0.09663 0.08171 -0.1556 0.6373 1.0010
3.750 0.9596 0.09651 0.08147 -0.1575 0.6323 1.0010
4.000 0.9983 0.09577 0.08059 -0.1618 0.6291 1.0010
4.250 1.0502 0.09418 0.07879 -0.1689 0.6264 1.0010
4.500 0.9294 0.10475 0.08972 -0.1377 0.6099 1.0010
4.750 0.9708 0.10384 0.08868 -0.1424 0.6069 1.0010
5.000 1.0238 0.10218 0.08687 -0.1495 0.6047 1.0010
6.000 0.8692 0.12676 0.11179 -0.1066 0.5618 1.0010
6.250 0.9032 0.12624 0.11119 -0.1095 0.5597 1.0010
6.500 0.9467 0.12466 0.10950 -0.1137 0.5580 1.0010
6.750 0.9930 0.12289 0.10762 -0.1186 0.5567 1.0010
7.250 0.9104 0.13887 0.12378 -0.1018 0.5323 1.0010
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Polar data table (+)
Polar graphs
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