AH 93-W-257 (ah93w257-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-257 (ah93w257-il) Reynolds number: 200,000 Max Cl/Cd: 58.29 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w257-il-200000-n5.txt Download as CSV file: xf-ah93w257-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9749 0.09562 0.08945 -0.0295 1.0000 0.1231
-17.250 -0.9722 0.09282 0.08669 -0.0305 1.0000 0.1269
-17.000 -0.9715 0.08972 0.08359 -0.0316 1.0000 0.1316
-16.750 -0.9698 0.08680 0.08067 -0.0326 1.0000 0.1364
-16.500 -0.9699 0.08370 0.07760 -0.0336 1.0000 0.1418
-16.250 -0.9691 0.08068 0.07457 -0.0345 1.0000 0.1475
-16.000 -0.9695 0.07761 0.07154 -0.0355 1.0000 0.1536
-15.750 -0.9693 0.07458 0.06850 -0.0364 1.0000 0.1602
-15.500 -0.9699 0.07156 0.06553 -0.0373 1.0000 0.1673
-15.250 -0.9701 0.06855 0.06253 -0.0382 1.0000 0.1746
-15.000 -0.9700 0.06565 0.05966 -0.0390 1.0000 0.1826
-14.750 -0.9697 0.06282 0.05685 -0.0398 1.0000 0.1901
-14.500 -0.9686 0.06007 0.05410 -0.0406 1.0000 0.1982
-14.250 -0.9604 0.05751 0.05142 -0.0428 0.8691 0.2063
-14.000 -0.9589 0.05499 0.04866 -0.0432 0.8207 0.2141
-13.750 -0.9538 0.05301 0.04661 -0.0435 0.7937 0.2213
-13.500 -0.9517 0.05057 0.04403 -0.0439 0.7745 0.2290
-13.250 -0.9447 0.04881 0.04223 -0.0441 0.7590 0.2358
-13.000 -0.9414 0.04660 0.03991 -0.0445 0.7456 0.2432
-12.750 -0.9334 0.04492 0.03819 -0.0447 0.7341 0.2498
-12.500 -0.9274 0.04304 0.03623 -0.0450 0.7234 0.2570
-12.250 -0.9204 0.04122 0.03433 -0.0454 0.7143 0.2636
-12.000 -0.9107 0.03975 0.03284 -0.0456 0.7051 0.2703
-11.750 -0.9067 0.03769 0.03063 -0.0460 0.6970 0.2774
-11.500 -0.8925 0.03672 0.02967 -0.0460 0.6897 0.2834
-11.250 -0.8848 0.03509 0.02800 -0.0463 0.6827 0.2903
-11.000 -0.8767 0.03358 0.02639 -0.0465 0.6764 0.2966
-10.750 -0.8630 0.03264 0.02543 -0.0465 0.6708 0.3027
-10.500 -0.8569 0.03092 0.02362 -0.0467 0.6659 0.3098
-10.250 -0.8421 0.03000 0.02271 -0.0468 0.6605 0.3156
-10.000 -0.8292 0.02894 0.02162 -0.0470 0.6554 0.3223
-9.750 -0.8243 0.02727 0.01983 -0.0471 0.6507 0.3297
-9.500 -0.8077 0.02684 0.01942 -0.0466 0.6462 0.3363
-9.250 -0.8017 0.02523 0.01771 -0.0473 0.6419 0.3447
-9.000 -0.7793 0.02477 0.01729 -0.0478 0.6372 0.3506
-8.750 -0.7572 0.02415 0.01664 -0.0487 0.6328 0.3562
-8.500 -0.7370 0.02285 0.01518 -0.0511 0.6289 0.3629
-8.250 -0.7104 0.02258 0.01489 -0.0518 0.6252 0.3671
-8.000 -0.6833 0.02234 0.01461 -0.0525 0.6219 0.3714
-7.750 -0.6557 0.02161 0.01381 -0.0547 0.6185 0.3771
-7.500 -0.6262 0.02077 0.01286 -0.0575 0.6147 0.3827
-7.250 -0.5976 0.02073 0.01286 -0.0578 0.6109 0.3862
-7.000 -0.5681 0.02048 0.01258 -0.0590 0.6072 0.3906
-6.750 -0.5369 0.01995 0.01194 -0.0613 0.6037 0.3961
-6.500 -0.5057 0.01950 0.01136 -0.0633 0.6007 0.4009
-6.250 -0.4766 0.01953 0.01138 -0.0636 0.5979 0.4042
-6.000 -0.4462 0.01940 0.01128 -0.0646 0.5952 0.4083
-5.750 -0.4145 0.01911 0.01094 -0.0663 0.5922 0.4132
-5.500 -0.3813 0.01867 0.01038 -0.0687 0.5891 0.4183
-5.250 -0.3520 0.01870 0.01046 -0.0689 0.5859 0.4213
-5.000 -0.3218 0.01869 0.01045 -0.0695 0.5828 0.4249
-4.750 -0.2903 0.01856 0.01027 -0.0707 0.5800 0.4293
-4.500 -0.2574 0.01832 0.00990 -0.0726 0.5774 0.4343
-4.250 -0.2258 0.01824 0.00975 -0.0738 0.5751 0.4382
-4.000 -0.1958 0.01829 0.00988 -0.0742 0.5727 0.4413
-3.750 -0.1647 0.01828 0.00989 -0.0750 0.5701 0.4450
-3.500 -0.1325 0.01817 0.00976 -0.0764 0.5673 0.4495
-3.250 -0.0983 0.01792 0.00940 -0.0785 0.5643 0.4547
-3.000 -0.0685 0.01798 0.00950 -0.0788 0.5616 0.4575
-2.750 -0.0383 0.01804 0.00958 -0.0793 0.5590 0.4604
-2.500 -0.0071 0.01807 0.00959 -0.0801 0.5568 0.4640
-2.250 0.0253 0.01804 0.00949 -0.0813 0.5547 0.4684
-2.000 0.0595 0.01790 0.00923 -0.0832 0.5526 0.4732
-1.750 0.0896 0.01796 0.00937 -0.0837 0.5503 0.4758
-1.500 0.1195 0.01806 0.00955 -0.0841 0.5476 0.4785
-1.250 0.1502 0.01813 0.00965 -0.0847 0.5448 0.4817
-1.000 0.1818 0.01815 0.00966 -0.0857 0.5421 0.4855
-0.750 0.2149 0.01807 0.00954 -0.0871 0.5398 0.4898
-0.500 0.2475 0.01802 0.00945 -0.0884 0.5376 0.4935
-0.250 0.2770 0.01816 0.00963 -0.0886 0.5356 0.4959
0.000 0.3072 0.01830 0.00977 -0.0890 0.5336 0.4986
0.250 0.3381 0.01842 0.00987 -0.0897 0.5315 0.5018
0.500 0.3693 0.01846 0.00996 -0.0906 0.5290 0.5052
0.750 0.4019 0.01844 0.00994 -0.0919 0.5264 0.5093
1.000 0.4338 0.01846 0.00997 -0.0930 0.5239 0.5129
1.250 0.4629 0.01863 0.01022 -0.0932 0.5215 0.5151
1.500 0.4925 0.01878 0.01041 -0.0935 0.5192 0.5175
1.750 0.5227 0.01888 0.01055 -0.0940 0.5169 0.5202
2.000 0.5536 0.01894 0.01060 -0.0947 0.5147 0.5233
2.250 0.5856 0.01898 0.01060 -0.0957 0.5126 0.5269
2.500 0.6196 0.01900 0.01052 -0.0972 0.5107 0.5313
2.750 0.6477 0.01919 0.01085 -0.0973 0.5084 0.5334
3.000 0.6761 0.01939 0.01117 -0.0975 0.5058 0.5355
3.250 0.7049 0.01957 0.01142 -0.0977 0.5029 0.5377
3.500 0.7343 0.01970 0.01161 -0.0981 0.5002 0.5402
3.750 0.7644 0.01982 0.01177 -0.0986 0.4978 0.5432
4.000 0.7954 0.01991 0.01186 -0.0994 0.4956 0.5469
4.250 0.8281 0.01993 0.01182 -0.1006 0.4935 0.5510
4.500 0.8581 0.02004 0.01195 -0.1010 0.4914 0.5531
4.750 0.8857 0.02027 0.01228 -0.1010 0.4888 0.5549
5.000 0.9128 0.02053 0.01268 -0.1010 0.4860 0.5570
5.250 0.9403 0.02076 0.01301 -0.1011 0.4829 0.5594
5.500 0.9686 0.02093 0.01325 -0.1013 0.4799 0.5622
5.750 0.9980 0.02105 0.01341 -0.1017 0.4773 0.5653
6.000 1.0285 0.02112 0.01348 -0.1024 0.4748 0.5685
6.250 1.0607 0.02116 0.01345 -0.1034 0.4724 0.5720
6.500 1.0875 0.02139 0.01378 -0.1033 0.4696 0.5739
6.750 1.1119 0.02170 0.01426 -0.1028 0.4658 0.5758
7.000 1.1374 0.02194 0.01462 -0.1025 0.4621 0.5778
7.250 1.1642 0.02209 0.01485 -0.1024 0.4585 0.5800
7.500 1.1923 0.02215 0.01493 -0.1025 0.4551 0.5824
7.750 1.2214 0.02220 0.01497 -0.1027 0.4516 0.5853
8.000 1.2438 0.02252 0.01544 -0.1022 0.4460 0.5884
8.250 1.2696 0.02267 0.01565 -0.1022 0.4408 0.5918
8.500 1.2965 0.02269 0.01567 -0.1021 0.4360 0.5941
8.750 1.3191 0.02289 0.01595 -0.1013 0.4305 0.5958
9.000 1.3381 0.02322 0.01642 -0.1001 0.4235 0.5976
9.250 1.3606 0.02334 0.01656 -0.0992 0.4173 0.5997
9.500 1.3781 0.02372 0.01706 -0.0978 0.4101 0.6021
9.750 1.3944 0.02407 0.01747 -0.0962 0.4020 0.6047
10.000 1.4087 0.02446 0.01789 -0.0944 0.3939 0.6073
10.250 1.4130 0.02505 0.01855 -0.0913 0.3848 0.6098
10.500 1.4222 0.02583 0.01933 -0.0893 0.3751 0.6124
10.750 1.4292 0.02690 0.02040 -0.0876 0.3640 0.6149
11.000 1.4319 0.02838 0.02197 -0.0858 0.3525 0.6166
11.250 1.4328 0.03018 0.02380 -0.0842 0.3405 0.6184
11.500 1.4304 0.03242 0.02604 -0.0829 0.3274 0.6202
11.750 1.4258 0.03506 0.02873 -0.0818 0.3131 0.6220
12.000 1.4192 0.03800 0.03166 -0.0808 0.2985 0.6238
12.250 1.4099 0.04124 0.03489 -0.0799 0.2835 0.6256
12.500 1.3986 0.04475 0.03837 -0.0790 0.2686 0.6274
12.750 1.3863 0.04840 0.04198 -0.0782 0.2538 0.6292
13.000 1.3736 0.05215 0.04568 -0.0775 0.2394 0.6309
13.250 1.3618 0.05599 0.04946 -0.0770 0.2252 0.6328
13.500 1.3510 0.05991 0.05333 -0.0767 0.2115 0.6348
13.750 1.3419 0.06376 0.05713 -0.0766 0.1982 0.6366
14.000 1.3343 0.06744 0.06080 -0.0764 0.1856 0.6380
14.250 1.3269 0.07119 0.06455 -0.0763 0.1739 0.6394
14.500 1.3204 0.07489 0.06823 -0.0762 0.1629 0.6408
14.750 1.3141 0.07865 0.07199 -0.0763 0.1527 0.6423
15.000 1.3088 0.08237 0.07569 -0.0765 0.1426 0.6438
15.250 1.3058 0.08588 0.07920 -0.0767 0.1332 0.6454
15.500 1.3027 0.08941 0.08273 -0.0770 0.1246 0.6471
15.750 1.2992 0.09308 0.08639 -0.0774 0.1167 0.6488
16.000 1.2969 0.09662 0.08992 -0.0779 0.1092 0.6506
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