AH 88-K-130/20 (ah88k130-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 88-K-130/20 (ah88k130-il) Reynolds number: 100,000 Max Cl/Cd: 42.95 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah88k130-il-100000-n5.txt Download as CSV file: xf-ah88k130-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1094 0.11751 0.11255 -0.0940 0.9380 0.0446
-12.250 -0.1046 0.11449 0.10952 -0.0957 0.9359 0.0460
-11.750 -0.2134 0.12162 0.11648 -0.0878 0.9506 0.0416
-11.500 -0.2025 0.11802 0.11287 -0.0905 0.9482 0.0426
-11.250 -0.1921 0.11437 0.10920 -0.0934 0.9460 0.0452
-11.000 -0.1831 0.11062 0.10544 -0.0972 0.9438 0.0472
-10.750 -0.1841 0.10744 0.10229 -0.1022 0.9391 0.0494
-10.500 -0.1820 0.10397 0.09883 -0.1070 0.9353 0.0499
-10.250 -0.1772 0.10016 0.09503 -0.1114 0.9324 0.0501
-10.000 -0.1732 0.09599 0.09085 -0.1161 0.9295 0.0502
-9.750 -0.1693 0.09158 0.08649 -0.1170 0.9262 0.0506
-9.500 -0.1577 0.08781 0.08271 -0.1159 0.9239 0.0516
-9.250 -0.1494 0.08451 0.07940 -0.1169 0.9209 0.0523
-8.750 -0.1371 0.07534 0.07017 -0.1220 0.9154 0.0342
-8.250 -0.1643 0.06494 0.05968 -0.1297 0.9036 0.0268
-8.000 -0.1724 0.06270 0.05741 -0.1284 0.8988 0.0262
-7.750 -0.1796 0.06010 0.05475 -0.1273 0.8938 0.0258
-7.500 -0.1803 0.05701 0.05152 -0.1273 0.8903 0.0252
-7.250 -0.1861 0.05458 0.04896 -0.1253 0.8854 0.0247
-7.000 -0.1896 0.05208 0.04630 -0.1232 0.8805 0.0243
-6.750 -0.1846 0.04889 0.04284 -0.1224 0.8771 0.0237
-6.500 -0.1793 0.04597 0.03963 -0.1209 0.8736 0.0232
-6.250 -0.1812 0.04404 0.03747 -0.1173 0.8679 0.0228
-6.000 -0.1692 0.04121 0.03426 -0.1161 0.8646 0.0225
-5.750 -0.1505 0.03825 0.03084 -0.1156 0.8623 0.0223
-5.500 -0.1439 0.03658 0.02885 -0.1126 0.8573 0.0223
-5.250 -0.1296 0.03481 0.02668 -0.1107 0.8532 0.0230
-5.000 -0.1053 0.03304 0.02447 -0.1104 0.8506 0.0252
-4.750 -0.0770 0.03134 0.02230 -0.1105 0.8488 0.0267
-4.500 -0.0525 0.02990 0.02051 -0.1098 0.8463 0.0274
-4.250 -0.0442 0.02905 0.01952 -0.1065 0.8402 0.0279
-4.000 -0.0197 0.02753 0.01790 -0.1060 0.8376 0.0295
-3.750 0.0079 0.02645 0.01674 -0.1061 0.8357 0.0320
-3.250 0.0428 0.02548 0.01564 -0.1030 0.8274 0.0415
-3.000 0.0663 0.02506 0.01510 -0.1023 0.8241 0.0502
-2.750 0.0939 0.02434 0.01433 -0.1026 0.8219 0.0615
-2.500 0.1238 0.02364 0.01369 -0.1032 0.8203 0.0900
-2.250 0.1312 0.02326 0.01380 -0.1003 0.8137 0.1921
-2.000 0.1400 0.02174 0.01410 -0.0971 0.8100 0.6299
-1.750 0.1486 0.02215 0.01483 -0.0910 0.8072 0.7847
-1.500 0.1458 0.02285 0.01552 -0.0843 0.8007 0.8395
-1.250 0.1404 0.02317 0.01586 -0.0759 0.7953 0.8855
-1.000 0.1554 0.02316 0.01576 -0.0711 0.7931 0.9304
-0.750 0.1956 0.02313 0.01549 -0.0733 0.7921 0.9427
-0.500 0.2038 0.02365 0.01594 -0.0709 0.7838 0.9535
-0.250 0.2371 0.02370 0.01582 -0.0724 0.7813 0.9595
0.000 0.2770 0.02371 0.01565 -0.0752 0.7797 0.9632
0.250 0.3169 0.02368 0.01549 -0.0779 0.7784 0.9670
0.750 0.3665 0.02448 0.01615 -0.0792 0.7677 0.9810
1.000 0.4045 0.02451 0.01610 -0.0816 0.7659 0.9852
1.250 0.4452 0.02451 0.01603 -0.0845 0.7646 0.9888
1.750 0.4673 0.02532 0.01681 -0.0806 0.7520 1.0000
2.000 0.4949 0.02527 0.01673 -0.0808 0.7502 1.0000
2.250 0.4846 0.02611 0.01756 -0.0755 0.7395 1.0000
2.500 0.5148 0.02612 0.01755 -0.0762 0.7373 1.0000
3.000 0.5504 0.02693 0.01839 -0.0745 0.7254 1.0000
3.250 0.5828 0.02690 0.01836 -0.0756 0.7234 1.0000
3.500 0.5911 0.02780 0.01929 -0.0737 0.7143 1.0000
3.750 0.6218 0.02784 0.01937 -0.0745 0.7116 1.0000
4.000 0.6506 0.02796 0.01953 -0.0751 0.7084 1.0000
4.250 0.6645 0.02870 0.02034 -0.0740 0.7000 1.0000
4.500 0.6972 0.02859 0.02031 -0.0750 0.6976 1.0000
5.000 0.7410 0.02936 0.02124 -0.0744 0.6854 1.0000
5.500 0.7881 0.02988 0.02200 -0.0741 0.6732 1.0000
5.750 0.8232 0.02940 0.02166 -0.0750 0.6703 1.0000
6.250 0.8729 0.02948 0.02205 -0.0745 0.6572 1.0000
6.500 0.8923 0.02969 0.02241 -0.0735 0.6474 1.0000
6.750 0.9366 0.02779 0.02069 -0.0743 0.6419 1.0000
7.000 0.9648 0.02688 0.01994 -0.0735 0.6280 1.0000
7.250 0.9815 0.02678 0.02000 -0.0717 0.6075 1.0000
7.500 1.0095 0.02587 0.01921 -0.0707 0.5828 1.0000
7.750 1.0306 0.02569 0.01913 -0.0693 0.5531 1.0000
8.000 1.0537 0.02548 0.01896 -0.0681 0.5144 1.0000
8.250 1.0764 0.02506 0.01795 -0.0660 0.4071 1.0000
8.500 1.0698 0.02700 0.01915 -0.0619 0.3048 1.0000
8.750 1.0599 0.02949 0.02100 -0.0582 0.2164 1.0000
9.000 1.0545 0.03192 0.02290 -0.0552 0.1363 1.0000
9.250 1.0557 0.03402 0.02461 -0.0530 0.0855 1.0000
9.500 1.0603 0.03596 0.02635 -0.0511 0.0569 1.0000
9.750 1.0665 0.03781 0.02820 -0.0494 0.0435 1.0000
10.000 1.0715 0.03981 0.03021 -0.0476 0.0370 1.0000
10.250 1.0782 0.04170 0.03225 -0.0460 0.0326 1.0000
10.500 1.0826 0.04381 0.03442 -0.0445 0.0286 1.0000
10.750 1.0891 0.04582 0.03657 -0.0431 0.0260 1.0000
11.000 1.0979 0.04775 0.03867 -0.0417 0.0241 1.0000
11.250 1.1082 0.04966 0.04071 -0.0405 0.0225 1.0000
11.500 1.1197 0.05156 0.04275 -0.0395 0.0208 1.0000
11.750 1.1313 0.05375 0.04495 -0.0387 0.0190 1.0000
12.000 1.1474 0.05550 0.04697 -0.0379 0.0175 1.0000
12.250 1.1655 0.05761 0.04931 -0.0371 0.0164 1.0000
12.500 1.1824 0.06004 0.05201 -0.0364 0.0157 1.0000
12.750 1.1948 0.06285 0.05510 -0.0355 0.0152 1.0000
13.000 1.2023 0.06600 0.05854 -0.0347 0.0148 1.0000
13.250 1.2047 0.06948 0.06233 -0.0338 0.0146 1.0000
13.500 1.2027 0.07321 0.06635 -0.0330 0.0143 1.0000
13.750 1.1972 0.07712 0.07054 -0.0324 0.0141 1.0000
14.000 1.1895 0.08118 0.07483 -0.0321 0.0138 1.0000
14.250 1.1797 0.08558 0.07947 -0.0322 0.0136 1.0000
14.500 1.1677 0.09045 0.08457 -0.0327 0.0134 1.0000
14.750 1.1538 0.09580 0.09016 -0.0337 0.0133 1.0000
15.000 1.1385 0.10156 0.09617 -0.0353 0.0132 1.0000
15.250 1.1223 0.10778 0.10263 -0.0375 0.0131 1.0000
15.500 1.1055 0.11446 0.10953 -0.0405 0.0131 1.0000
15.750 1.0882 0.12179 0.11711 -0.0444 0.0133 1.0000
16.000 1.0664 0.13099 0.12657 -0.0499 0.0135 1.0000
16.250 1.0140 0.15164 0.14759 -0.0634 0.0152 1.0000
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