AH 88-K-130/20 (ah88k130-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 88-K-130/20 (ah88k130-il) Reynolds number: 200,000 Max Cl/Cd: 80.36 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah88k130-il-200000.txt Download as CSV file: xf-ah88k130-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 88-K-130/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1316 0.09393 0.09026 -0.1144 0.9535 0.0358
-10.000 -0.1273 0.08983 0.08618 -0.1203 0.9501 0.0376
-9.750 -0.1228 0.08546 0.08181 -0.1273 0.9470 0.0382
-9.000 -0.1075 0.07419 0.07058 -0.1316 0.9390 0.0410
-8.750 -0.0999 0.07208 0.06848 -0.1321 0.9361 0.0443
-8.500 -0.0996 0.06803 0.06444 -0.1364 0.9322 0.0456
-8.250 -0.1102 0.06451 0.06091 -0.1391 0.9271 0.0458
-8.000 -0.1286 0.06243 0.05880 -0.1383 0.9209 0.0469
-7.750 -0.1354 0.05938 0.05560 -0.1398 0.9168 0.0483
-7.500 -0.1534 0.05848 0.05462 -0.1357 0.9106 0.0488
-7.250 -0.1655 0.05840 0.05412 -0.1332 0.9052 0.0501
-6.500 -0.1704 0.04953 0.04525 -0.1262 0.8925 0.0537
-6.250 -0.1524 0.04699 0.04255 -0.1269 0.8903 0.0570
-6.000 -0.1676 0.04666 0.04213 -0.1204 0.8829 0.0585
-5.750 -0.1615 0.04434 0.03927 -0.1186 0.8783 0.0648
-5.500 -0.1357 0.04145 0.03642 -0.1200 0.8768 0.0682
-5.250 -0.1501 0.04134 0.03626 -0.1132 0.8687 0.0700
-5.000 -0.1310 0.03910 0.03366 -0.1130 0.8653 0.0797
-4.750 -0.1009 0.03707 0.03131 -0.1146 0.8635 0.0929
-4.500 -0.0694 0.03489 0.02893 -0.1164 0.8622 0.1072
-4.250 -0.0695 0.03022 0.02322 -0.1063 0.8537 0.0361
-4.000 -0.0364 0.02783 0.02048 -0.1070 0.8517 0.0337
-3.750 0.0009 0.02610 0.01845 -0.1083 0.8504 0.0343
-3.500 0.0376 0.02523 0.01734 -0.1097 0.8491 0.0379
-3.250 0.0341 0.02549 0.01753 -0.1042 0.8410 0.0385
-3.000 0.0610 0.02388 0.01599 -0.1041 0.8383 0.0419
-2.750 0.0965 0.02315 0.01520 -0.1055 0.8366 0.0503
-2.500 0.1322 0.02212 0.01426 -0.1075 0.8352 0.0720
-2.250 0.1365 0.02231 0.01444 -0.1037 0.8277 0.0859
-2.000 0.1481 0.01991 0.01474 -0.1013 0.8244 0.7198
-1.750 0.1716 0.02038 0.01516 -0.0991 0.8221 0.8106
-1.500 0.1962 0.02062 0.01530 -0.0972 0.8205 0.8396
-1.250 0.1847 0.02140 0.01609 -0.0899 0.8102 0.8551
-1.000 0.1947 0.02151 0.01617 -0.0845 0.8076 0.8861
-0.750 0.1778 0.02214 0.01683 -0.0759 0.7984 0.9079
-0.500 0.1733 0.02201 0.01670 -0.0676 0.7944 0.9432
-0.250 0.2478 0.02228 0.01684 -0.0755 0.7951 0.9747
0.000 0.3101 0.02231 0.01671 -0.0826 0.7948 0.9780
0.250 0.3591 0.02222 0.01651 -0.0871 0.7940 0.9803
0.500 0.4039 0.02211 0.01632 -0.0908 0.7931 0.9829
0.750 0.4491 0.02199 0.01613 -0.0945 0.7923 0.9851
1.000 0.4951 0.02186 0.01594 -0.0984 0.7917 0.9868
1.250 0.5069 0.02289 0.01699 -0.0977 0.7812 0.9954
1.500 0.5510 0.02275 0.01683 -0.1012 0.7801 0.9975
1.750 0.5947 0.02257 0.01662 -0.1046 0.7791 0.9996
2.000 0.6321 0.02228 0.01633 -0.1064 0.7781 1.0000
2.250 0.5190 0.02413 0.01818 -0.0825 0.7547 1.0000
2.500 0.5490 0.02398 0.01803 -0.0831 0.7527 1.0000
2.750 0.5837 0.02379 0.01785 -0.0844 0.7514 1.0000
3.000 0.6221 0.02352 0.01759 -0.0863 0.7505 1.0000
3.250 0.6596 0.02328 0.01738 -0.0881 0.7494 1.0000
3.500 0.6493 0.02432 0.01843 -0.0829 0.7377 1.0000
3.750 0.6780 0.02439 0.01853 -0.0835 0.7343 1.0000
4.000 0.7271 0.02362 0.01784 -0.0867 0.7355 1.0000
4.500 0.7412 0.02550 0.01980 -0.0825 0.7158 1.0000
4.750 0.7829 0.02465 0.01902 -0.0843 0.7135 1.0000
5.000 0.8410 0.02249 0.01699 -0.0875 0.7130 1.0000
5.250 0.8959 0.02070 0.01531 -0.0908 0.7120 1.0000
5.500 0.9544 0.01873 0.01347 -0.0947 0.7105 1.0000
5.750 0.9756 0.01831 0.01316 -0.0934 0.7006 1.0000
6.000 1.0316 0.01642 0.01138 -0.0970 0.6965 1.0000
6.250 1.0591 0.01562 0.01068 -0.0964 0.6836 1.0000
6.500 1.0910 0.01483 0.01001 -0.0965 0.6689 1.0000
6.750 1.1097 0.01456 0.00980 -0.0946 0.6466 1.0000
7.000 1.1365 0.01421 0.00943 -0.0940 0.6168 1.0000
7.250 1.1515 0.01433 0.00939 -0.0915 0.5674 1.0000
7.500 1.1539 0.01506 0.00979 -0.0872 0.4937 1.0000
7.750 1.1414 0.01664 0.01085 -0.0813 0.4096 1.0000
8.000 1.1260 0.01874 0.01246 -0.0758 0.3320 1.0000
8.250 1.1112 0.02115 0.01439 -0.0709 0.2497 1.0000
8.500 1.0973 0.02379 0.01646 -0.0666 0.1615 1.0000
8.750 1.0848 0.02660 0.01867 -0.0626 0.0827 1.0000
9.000 1.0795 0.02913 0.02092 -0.0593 0.0501 1.0000
9.250 1.0827 0.03107 0.02286 -0.0570 0.0393 1.0000
9.500 1.0860 0.03306 0.02495 -0.0548 0.0351 1.0000
9.750 1.0932 0.03481 0.02676 -0.0531 0.0317 1.0000
10.000 1.0968 0.03701 0.02897 -0.0510 0.0283 1.0000
10.250 1.1096 0.03862 0.03067 -0.0496 0.0261 1.0000
10.500 1.1268 0.04008 0.03224 -0.0485 0.0243 1.0000
10.750 1.1493 0.04154 0.03378 -0.0477 0.0228 1.0000
11.000 1.1752 0.04309 0.03545 -0.0473 0.0214 1.0000
11.250 1.2218 0.04614 0.03862 -0.0487 0.0189 1.0000
11.500 1.2409 0.04846 0.04124 -0.0479 0.0185 1.0000
11.750 1.2594 0.05172 0.04487 -0.0470 0.0183 1.0000
12.000 1.2722 0.05592 0.04944 -0.0459 0.0185 1.0000
12.250 1.2913 0.06227 0.05615 -0.0456 0.0193 1.0000
12.500 1.2883 0.06408 0.05817 -0.0432 0.0196 1.0000
12.750 1.2542 0.06897 0.06390 -0.0379 0.0226 1.0000
13.000 1.2327 0.07513 0.07044 -0.0357 0.0245 1.0000
13.250 1.2134 0.08089 0.07645 -0.0344 0.0258 1.0000
13.500 1.0873 0.07620 0.07199 -0.0252 0.0211 1.0000
13.750 1.0450 0.08128 0.07744 -0.0242 0.0217 1.0000
14.000 1.0090 0.08720 0.08369 -0.0248 0.0224 1.0000
14.250 0.9770 0.09336 0.09011 -0.0265 0.0229 1.0000
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Polar data table (+)
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