AH 81-K-144/17 (ah81k144-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 81-K-144/17 (ah81k144-il) Reynolds number: 200,000 Max Cl/Cd: 67.39 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah81k144-il-200000-n5.txt Download as CSV file: xf-ah81k144-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 81-K-144/17
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1829 0.09331 0.08844 -0.0982 0.7679 0.0149
-11.000 -0.1864 0.08848 0.08363 -0.1004 0.7671 0.0150
-10.750 -0.1925 0.08333 0.07853 -0.1027 0.7659 0.0150
-10.500 -0.2003 0.07800 0.07327 -0.1052 0.7647 0.0145
-10.250 -0.3261 0.04858 0.04373 -0.1228 0.7628 0.0131
-10.000 -0.3239 0.04744 0.04259 -0.1226 0.7611 0.0136
-9.750 -0.3600 0.04288 0.03777 -0.1200 0.7589 0.0134
-9.500 -0.3812 0.03997 0.03458 -0.1161 0.7571 0.0133
-9.250 -0.3868 0.03762 0.03197 -0.1134 0.7556 0.0135
-9.000 -0.3861 0.03547 0.02953 -0.1111 0.7544 0.0137
-8.750 -0.3837 0.03299 0.02667 -0.1088 0.7533 0.0137
-8.500 -0.3712 0.03186 0.02534 -0.1074 0.7521 0.0146
-8.250 -0.3609 0.02994 0.02312 -0.1056 0.7505 0.0146
-8.000 -0.3466 0.02856 0.02144 -0.1041 0.7487 0.0159
-7.750 -0.3305 0.02708 0.01965 -0.1027 0.7470 0.0163
-7.500 -0.3122 0.02570 0.01798 -0.1015 0.7454 0.0166
-7.250 -0.2929 0.02440 0.01650 -0.1006 0.7440 0.0170
-7.000 -0.2728 0.02330 0.01529 -0.0997 0.7428 0.0175
-6.750 -0.2516 0.02249 0.01437 -0.0989 0.7416 0.0184
-6.500 -0.2295 0.02174 0.01351 -0.0982 0.7405 0.0193
-6.250 -0.2073 0.02099 0.01263 -0.0975 0.7394 0.0205
-6.000 -0.1843 0.02039 0.01188 -0.0968 0.7383 0.0218
-5.750 -0.1629 0.01986 0.01135 -0.0960 0.7368 0.0243
-5.500 -0.1409 0.01949 0.01093 -0.0953 0.7349 0.0270
-5.250 -0.1193 0.01900 0.01039 -0.0944 0.7332 0.0294
-5.000 -0.0968 0.01864 0.01002 -0.0938 0.7316 0.0342
-4.750 -0.0741 0.01822 0.00960 -0.0931 0.7299 0.0415
-4.500 -0.0508 0.01786 0.00920 -0.0925 0.7283 0.0506
-4.250 -0.0270 0.01754 0.00889 -0.0920 0.7270 0.0636
-4.000 -0.0030 0.01725 0.00864 -0.0915 0.7258 0.0824
-3.750 0.0211 0.01696 0.00843 -0.0911 0.7248 0.1081
-3.500 0.0454 0.01668 0.00822 -0.0907 0.7238 0.1392
-3.250 0.0686 0.01646 0.00810 -0.0902 0.7223 0.1726
-3.000 0.0892 0.01635 0.00815 -0.0893 0.7196 0.2098
-2.750 0.1107 0.01620 0.00815 -0.0885 0.7174 0.2556
-2.500 0.1316 0.01592 0.00810 -0.0876 0.7155 0.3227
-2.250 0.1506 0.01548 0.00803 -0.0863 0.7137 0.4249
-2.000 0.1678 0.01497 0.00799 -0.0844 0.7121 0.5521
-1.750 0.1857 0.01462 0.00818 -0.0820 0.7108 0.6878
-1.500 0.2094 0.01469 0.00843 -0.0804 0.7098 0.7729
-1.250 0.2341 0.01478 0.00846 -0.0795 0.7087 0.8080
-1.000 0.2522 0.01512 0.00879 -0.0778 0.7055 0.8293
-0.750 0.2720 0.01539 0.00904 -0.0763 0.7024 0.8464
-0.500 0.2942 0.01553 0.00915 -0.0752 0.7002 0.8615
-0.250 0.3175 0.01561 0.00918 -0.0742 0.6984 0.8747
0.000 0.3421 0.01563 0.00916 -0.0733 0.6969 0.8879
0.250 0.3671 0.01563 0.00912 -0.0724 0.6957 0.9040
0.500 0.3960 0.01559 0.00906 -0.0722 0.6946 0.9204
0.750 0.4210 0.01577 0.00926 -0.0718 0.6919 0.9336
1.000 0.4486 0.01609 0.00960 -0.0724 0.6878 0.9415
1.250 0.4776 0.01617 0.00966 -0.0730 0.6854 0.9483
1.500 0.5139 0.01618 0.00963 -0.0749 0.6837 0.9525
1.750 0.5479 0.01613 0.00956 -0.0764 0.6822 0.9568
2.000 0.5806 0.01606 0.00946 -0.0776 0.6810 0.9609
2.250 0.6178 0.01598 0.00936 -0.0796 0.6799 0.9630
2.500 0.6437 0.01651 0.00998 -0.0804 0.6745 0.9678
2.750 0.6736 0.01661 0.01010 -0.0814 0.6713 0.9720
3.000 0.7084 0.01658 0.01008 -0.0831 0.6692 0.9743
3.250 0.7438 0.01647 0.00999 -0.0848 0.6676 0.9765
3.500 0.7786 0.01633 0.00986 -0.0864 0.6662 0.9787
4.000 0.8367 0.01687 0.01057 -0.0886 0.6572 0.9870
4.250 0.8692 0.01680 0.01054 -0.0898 0.6547 0.9904
4.500 0.9038 0.01663 0.01042 -0.0913 0.6529 0.9935
4.750 0.9333 0.01644 0.01027 -0.0917 0.6512 1.0000
5.000 0.9233 0.01717 0.01110 -0.0856 0.6427 1.0000
5.250 0.9467 0.01698 0.01094 -0.0848 0.6396 1.0000
5.500 0.9749 0.01669 0.01070 -0.0848 0.6375 1.0000
5.750 0.9753 0.01736 0.01146 -0.0806 0.6288 1.0000
6.000 1.0011 0.01718 0.01134 -0.0803 0.6253 1.0000
6.250 1.0331 0.01680 0.01102 -0.0808 0.6227 1.0000
6.500 1.0322 0.01759 0.01191 -0.0766 0.6127 1.0000
6.750 1.0647 0.01716 0.01156 -0.0772 0.6090 1.0000
7.000 1.0628 0.01796 0.01244 -0.0728 0.5987 1.0000
7.250 1.0813 0.01800 0.01255 -0.0714 0.5897 1.0000
7.500 1.1091 0.01712 0.01160 -0.0706 0.5652 1.0000
7.750 1.1287 0.01675 0.01100 -0.0687 0.5216 1.0000
8.000 1.1354 0.01735 0.01127 -0.0656 0.4701 1.0000
8.250 1.1379 0.01855 0.01227 -0.0627 0.4324 1.0000
8.500 1.1377 0.02008 0.01359 -0.0600 0.3938 1.0000
8.750 1.1350 0.02186 0.01516 -0.0572 0.3539 1.0000
9.000 1.1290 0.02392 0.01698 -0.0542 0.3096 1.0000
9.250 1.1212 0.02621 0.01898 -0.0513 0.2615 1.0000
9.500 1.1120 0.02868 0.02112 -0.0485 0.2092 1.0000
9.750 1.1046 0.03113 0.02326 -0.0459 0.1583 1.0000
10.000 1.0990 0.03353 0.02536 -0.0436 0.1117 1.0000
10.250 1.0981 0.03567 0.02729 -0.0418 0.0779 1.0000
10.500 1.1000 0.03769 0.02920 -0.0403 0.0557 1.0000
10.750 1.1065 0.03942 0.03091 -0.0391 0.0456 1.0000
11.000 1.1127 0.04122 0.03271 -0.0380 0.0386 1.0000
11.250 1.1205 0.04292 0.03447 -0.0370 0.0343 1.0000
11.500 1.1267 0.04481 0.03638 -0.0361 0.0301 1.0000
11.750 1.1348 0.04657 0.03824 -0.0353 0.0283 1.0000
12.000 1.1415 0.04847 0.04022 -0.0345 0.0262 1.0000
12.250 1.1468 0.05053 0.04236 -0.0336 0.0247 1.0000
12.500 1.1494 0.05290 0.04480 -0.0327 0.0235 1.0000
12.750 1.1569 0.05484 0.04685 -0.0321 0.0221 1.0000
13.000 1.1623 0.05699 0.04910 -0.0314 0.0212 1.0000
13.250 1.1689 0.05904 0.05123 -0.0309 0.0202 1.0000
13.500 1.1738 0.06130 0.05355 -0.0303 0.0191 1.0000
13.750 1.1768 0.06375 0.05606 -0.0297 0.0183 1.0000
14.000 1.1794 0.06623 0.05860 -0.0289 0.0176 1.0000
14.250 1.1866 0.06830 0.06080 -0.0284 0.0169 1.0000
14.500 1.1932 0.07040 0.06301 -0.0279 0.0163 1.0000
14.750 1.1995 0.07259 0.06533 -0.0275 0.0155 1.0000
15.000 1.2052 0.07486 0.06769 -0.0272 0.0149 1.0000
15.250 1.2102 0.07732 0.07021 -0.0272 0.0141 1.0000
15.500 1.2152 0.07965 0.07262 -0.0268 0.0138 1.0000
15.750 1.2190 0.08205 0.07507 -0.0262 0.0133 1.0000
16.000 1.2240 0.08448 0.07766 -0.0259 0.0128 1.0000
16.250 1.2289 0.08694 0.08028 -0.0255 0.0126 1.0000
16.500 1.2319 0.08977 0.08330 -0.0254 0.0121 1.0000
16.750 1.2346 0.09265 0.08634 -0.0255 0.0119 1.0000
17.000 1.2344 0.09604 0.08993 -0.0259 0.0114 1.0000
17.250 1.2333 0.09963 0.09369 -0.0266 0.0109 1.0000
17.500 1.2324 0.10322 0.09741 -0.0275 0.0106 1.0000
17.750 1.2306 0.10701 0.10130 -0.0287 0.0102 1.0000
18.000 1.2271 0.11104 0.10553 -0.0294 0.0102 1.0000
18.250 1.2246 0.11506 0.10964 -0.0309 0.0100 1.0000
18.500 1.2208 0.11924 0.11391 -0.0325 0.0097 1.0000
18.750 1.2146 0.12400 0.11885 -0.0341 0.0097 1.0000
19.000 1.2067 0.12920 0.12422 -0.0363 0.0096 1.0000
19.250 1.1926 0.13603 0.13133 -0.0396 0.0094 1.0000
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Polar data table (+)
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