AH 93-W-257 (ah93w257-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-W-257 (ah93w257-il) Reynolds number: 500,000 Max Cl/Cd: 92.54 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93w257-il-500000.txt Download as CSV file: xf-ah93w257-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-257
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0809 0.08953 0.08470 -0.0279 1.0000 0.1080
-17.750 -1.0792 0.08664 0.08179 -0.0288 1.0000 0.1111
-17.500 -1.0759 0.08399 0.07911 -0.0297 1.0000 0.1143
-17.250 -1.0774 0.08081 0.07597 -0.0306 1.0000 0.1181
-17.000 -1.0768 0.07786 0.07300 -0.0314 1.0000 0.1222
-16.750 -1.0777 0.07482 0.06998 -0.0323 1.0000 0.1268
-16.500 -1.0802 0.07159 0.06676 -0.0331 1.0000 0.1321
-16.250 -1.0824 0.06844 0.06363 -0.0339 1.0000 0.1380
-16.000 -1.0857 0.06523 0.06043 -0.0346 1.0000 0.1449
-15.750 -1.0908 0.06186 0.05711 -0.0354 1.0000 0.1522
-15.500 -1.0937 0.05876 0.05402 -0.0360 1.0000 0.1603
-15.250 -1.0983 0.05556 0.05086 -0.0366 1.0000 0.1692
-15.000 -1.1034 0.05233 0.04768 -0.0372 1.0000 0.1779
-14.750 -1.1027 0.04973 0.04509 -0.0377 1.0000 0.1870
-14.500 -1.1062 0.04677 0.04217 -0.0382 1.0000 0.1961
-14.250 -1.1058 0.04422 0.03967 -0.0386 1.0000 0.2046
-14.000 -1.0953 0.04203 0.03711 -0.0405 0.8359 0.2141
-13.750 -1.0960 0.03976 0.03472 -0.0404 0.7978 0.2221
-13.500 -1.0897 0.03796 0.03276 -0.0405 0.7725 0.2297
-13.250 -1.0872 0.03588 0.03065 -0.0407 0.7537 0.2374
-13.000 -1.0796 0.03417 0.02883 -0.0409 0.7383 0.2446
-12.750 -1.0736 0.03241 0.02705 -0.0411 0.7253 0.2515
-12.500 -1.0657 0.03074 0.02531 -0.0413 0.7145 0.2587
-12.250 -1.0564 0.02926 0.02380 -0.0415 0.7047 0.2653
-12.000 -1.0490 0.02768 0.02217 -0.0417 0.6956 0.2724
-11.750 -1.0371 0.02643 0.02085 -0.0419 0.6883 0.2787
-11.500 -1.0291 0.02496 0.01940 -0.0419 0.6811 0.2854
-11.250 -1.0171 0.02378 0.01814 -0.0420 0.6741 0.2919
-11.000 -1.0066 0.02263 0.01694 -0.0419 0.6677 0.2976
-10.750 -0.9967 0.02150 0.01584 -0.0418 0.6623 0.3040
-10.500 -0.9785 0.02047 0.01473 -0.0428 0.6566 0.3104
-10.250 -0.9582 0.01953 0.01377 -0.0441 0.6512 0.3167
-10.000 -0.9345 0.01868 0.01285 -0.0459 0.6454 0.3233
-9.750 -0.9072 0.01788 0.01198 -0.0481 0.6418 0.3292
-9.500 -0.8792 0.01714 0.01128 -0.0501 0.6376 0.3356
-9.250 -0.8485 0.01647 0.01056 -0.0527 0.6333 0.3422
-9.000 -0.8166 0.01589 0.00988 -0.0552 0.6289 0.3480
-8.750 -0.7845 0.01541 0.00939 -0.0575 0.6242 0.3544
-8.500 -0.7496 0.01492 0.00882 -0.0605 0.6201 0.3615
-8.250 -0.7159 0.01450 0.00841 -0.0629 0.6168 0.3690
-8.000 -0.6824 0.01422 0.00812 -0.0650 0.6134 0.3758
-7.750 -0.6486 0.01398 0.00777 -0.0670 0.6100 0.3808
-7.500 -0.6171 0.01377 0.00756 -0.0682 0.6067 0.3856
-7.250 -0.5852 0.01363 0.00740 -0.0695 0.6033 0.3902
-7.000 -0.5525 0.01354 0.00723 -0.0709 0.5994 0.3948
-6.750 -0.5190 0.01339 0.00700 -0.0726 0.5966 0.3991
-6.500 -0.4873 0.01321 0.00685 -0.0737 0.5939 0.4035
-6.250 -0.4553 0.01308 0.00675 -0.0748 0.5910 0.4077
-6.000 -0.4226 0.01298 0.00661 -0.0761 0.5881 0.4121
-5.750 -0.3895 0.01288 0.00644 -0.0775 0.5853 0.4164
-5.500 -0.3572 0.01276 0.00629 -0.0787 0.5826 0.4204
-5.250 -0.3256 0.01271 0.00624 -0.0796 0.5799 0.4244
-5.000 -0.2934 0.01273 0.00623 -0.0807 0.5765 0.4285
-4.750 -0.2606 0.01270 0.00616 -0.0819 0.5740 0.4328
-4.500 -0.2273 0.01261 0.00602 -0.0833 0.5718 0.4365
-4.250 -0.1959 0.01251 0.00597 -0.0841 0.5693 0.4406
-4.000 -0.1639 0.01247 0.00596 -0.0851 0.5669 0.4445
-3.750 -0.1315 0.01245 0.00592 -0.0861 0.5645 0.4486
-3.500 -0.0987 0.01243 0.00585 -0.0873 0.5621 0.4527
-3.250 -0.0662 0.01239 0.00576 -0.0884 0.5598 0.4563
-3.000 -0.0348 0.01240 0.00579 -0.0891 0.5572 0.4603
-2.750 -0.0031 0.01252 0.00589 -0.0900 0.5540 0.4640
-2.500 0.0292 0.01255 0.00592 -0.0909 0.5519 0.4680
-2.250 0.0619 0.01254 0.00588 -0.0920 0.5500 0.4719
-2.000 0.0941 0.01250 0.00585 -0.0930 0.5480 0.4755
-1.750 0.1255 0.01250 0.00590 -0.0937 0.5458 0.4790
-1.500 0.1572 0.01253 0.00596 -0.0945 0.5436 0.4825
-1.250 0.1891 0.01257 0.00599 -0.0953 0.5413 0.4862
-1.000 0.2214 0.01260 0.00597 -0.0963 0.5390 0.4899
-0.750 0.2539 0.01263 0.00594 -0.0973 0.5366 0.4928
-0.500 0.2848 0.01267 0.00601 -0.0979 0.5341 0.4964
-0.250 0.3160 0.01288 0.00623 -0.0986 0.5314 0.4996
0.000 0.3474 0.01292 0.00632 -0.0993 0.5299 0.5030
0.250 0.3792 0.01296 0.00638 -0.1001 0.5281 0.5064
0.500 0.4112 0.01299 0.00640 -0.1009 0.5259 0.5096
0.750 0.4432 0.01301 0.00641 -0.1018 0.5235 0.5126
1.000 0.4740 0.01301 0.00647 -0.1023 0.5212 0.5160
1.250 0.5051 0.01308 0.00657 -0.1029 0.5191 0.5188
1.500 0.5362 0.01316 0.00667 -0.1035 0.5171 0.5217
1.750 0.5675 0.01326 0.00675 -0.1042 0.5149 0.5247
2.000 0.5989 0.01343 0.00688 -0.1049 0.5123 0.5279
2.250 0.6305 0.01360 0.00704 -0.1057 0.5099 0.5307
2.500 0.6614 0.01357 0.00708 -0.1063 0.5081 0.5339
2.750 0.6919 0.01363 0.00721 -0.1068 0.5061 0.5365
3.000 0.7225 0.01371 0.00734 -0.1073 0.5038 0.5390
3.250 0.7531 0.01378 0.00745 -0.1078 0.5014 0.5416
3.500 0.7840 0.01385 0.00753 -0.1083 0.4990 0.5444
3.750 0.8150 0.01393 0.00761 -0.1089 0.4968 0.5474
4.000 0.8462 0.01404 0.00770 -0.1095 0.4945 0.5501
4.250 0.8772 0.01421 0.00783 -0.1102 0.4917 0.5527
4.500 0.9072 0.01431 0.00800 -0.1106 0.4894 0.5553
4.750 0.9369 0.01437 0.00816 -0.1109 0.4873 0.5575
5.000 0.9666 0.01446 0.00832 -0.1112 0.4847 0.5600
5.250 0.9965 0.01454 0.00845 -0.1116 0.4820 0.5626
5.500 1.0267 0.01462 0.00856 -0.1120 0.4794 0.5654
5.750 1.0571 0.01468 0.00862 -0.1124 0.4767 0.5680
6.000 1.0876 0.01480 0.00870 -0.1129 0.4739 0.5704
6.250 1.1178 0.01501 0.00890 -0.1134 0.4705 0.5725
6.500 1.1464 0.01495 0.00896 -0.1136 0.4674 0.5754
6.750 1.1750 0.01497 0.00907 -0.1136 0.4635 0.5777
7.000 1.2039 0.01500 0.00914 -0.1138 0.4597 0.5798
7.250 1.2328 0.01506 0.00920 -0.1139 0.4559 0.5820
7.500 1.2615 0.01522 0.00936 -0.1140 0.4513 0.5845
7.750 1.2892 0.01524 0.00948 -0.1140 0.4468 0.5872
8.000 1.3174 0.01528 0.00956 -0.1140 0.4418 0.5898
8.250 1.3454 0.01535 0.00960 -0.1140 0.4365 0.5919
8.500 1.3727 0.01544 0.00972 -0.1140 0.4305 0.5939
8.750 1.3993 0.01544 0.00980 -0.1138 0.4233 0.5964
9.000 1.4245 0.01559 0.00994 -0.1133 0.4165 0.5986
9.250 1.4502 0.01575 0.01021 -0.1130 0.4099 0.6009
9.500 1.4747 0.01595 0.01043 -0.1124 0.4019 0.6032
9.750 1.4982 0.01619 0.01070 -0.1118 0.3935 0.6055
10.000 1.5205 0.01647 0.01098 -0.1109 0.3832 0.6078
10.250 1.5418 0.01680 0.01133 -0.1100 0.3729 0.6103
10.500 1.5589 0.01729 0.01177 -0.1084 0.3614 0.6126
10.750 1.5749 0.01780 0.01227 -0.1067 0.3481 0.6144
11.000 1.5834 0.01836 0.01284 -0.1039 0.3346 0.6168
11.250 1.5841 0.01925 0.01371 -0.1000 0.3203 0.6188
11.500 1.5851 0.02058 0.01502 -0.0970 0.3040 0.6206
11.750 1.5814 0.02248 0.01690 -0.0943 0.2869 0.6224
12.000 1.5739 0.02509 0.01948 -0.0923 0.2695 0.6243
12.250 1.5635 0.02830 0.02267 -0.0907 0.2528 0.6262
12.500 1.5505 0.03194 0.02629 -0.0895 0.2372 0.6282
12.750 1.5356 0.03583 0.03015 -0.0882 0.2228 0.6300
13.000 1.5187 0.03993 0.03423 -0.0870 0.2098 0.6317
13.250 1.5015 0.04407 0.03835 -0.0858 0.1974 0.6332
13.500 1.4875 0.04794 0.04220 -0.0848 0.1855 0.6345
13.750 1.4749 0.05181 0.04606 -0.0840 0.1744 0.6357
14.000 1.4635 0.05570 0.04992 -0.0834 0.1638 0.6369
14.250 1.4519 0.05974 0.05394 -0.0830 0.1535 0.6388
14.500 1.4432 0.06352 0.05772 -0.0826 0.1433 0.6403
14.750 1.4363 0.06715 0.06135 -0.0823 0.1336 0.6418
15.000 1.4291 0.07090 0.06510 -0.0821 0.1249 0.6434
15.250 1.4230 0.07455 0.06874 -0.0819 0.1165 0.6450
15.750 1.4125 0.08181 0.07599 -0.0818 0.1011 0.6485
16.000 1.4090 0.08533 0.07951 -0.0819 0.0943 0.6504
16.250 1.4045 0.08898 0.08315 -0.0821 0.0880 0.6521
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