AH 81-K-144/17 (ah81k144-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 81-K-144/17 (ah81k144-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.28 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah81k144-il-1000000-n5.txt Download as CSV file: xf-ah81k144-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6797 0.04131 0.03769 -0.1139 0.7222 0.0048
-13.500 -0.6930 0.03588 0.03204 -0.1187 0.7212 0.0047
-13.250 -0.6986 0.03262 0.02862 -0.1202 0.7202 0.0048
-13.000 -0.7070 0.02959 0.02539 -0.1202 0.7190 0.0048
-12.750 -0.7028 0.02791 0.02358 -0.1195 0.7177 0.0047
-12.500 -0.6957 0.02659 0.02213 -0.1184 0.7165 0.0047
-12.250 -0.7016 0.02459 0.01996 -0.1153 0.7153 0.0048
-12.000 -0.6921 0.02382 0.01911 -0.1133 0.7143 0.0049
-11.750 -0.6800 0.02306 0.01827 -0.1116 0.7132 0.0051
-11.500 -0.6681 0.02209 0.01718 -0.1099 0.7123 0.0051
-11.250 -0.6567 0.02100 0.01592 -0.1081 0.7112 0.0051
-11.000 -0.6394 0.02033 0.01517 -0.1069 0.7102 0.0053
-10.750 -0.6218 0.01965 0.01438 -0.1058 0.7092 0.0054
-10.500 -0.6062 0.01873 0.01333 -0.1044 0.7081 0.0054
-10.250 -0.5880 0.01798 0.01248 -0.1032 0.7074 0.0055
-10.000 -0.5658 0.01759 0.01204 -0.1026 0.7064 0.0058
-9.750 -0.5466 0.01687 0.01122 -0.1016 0.7054 0.0059
-9.500 -0.5258 0.01629 0.01054 -0.1007 0.7045 0.0060
-9.250 -0.5041 0.01575 0.00992 -0.1000 0.7035 0.0062
-9.000 -0.4814 0.01531 0.00941 -0.0994 0.7025 0.0063
-8.750 -0.4596 0.01476 0.00878 -0.0986 0.7016 0.0063
-8.500 -0.4359 0.01438 0.00834 -0.0981 0.7006 0.0066
-8.250 -0.4136 0.01385 0.00773 -0.0974 0.6996 0.0065
-8.000 -0.3910 0.01332 0.00712 -0.0967 0.6986 0.0069
-7.750 -0.3673 0.01292 0.00666 -0.0962 0.6975 0.0071
-7.500 -0.3433 0.01253 0.00622 -0.0957 0.6965 0.0073
-7.250 -0.3186 0.01223 0.00587 -0.0954 0.6955 0.0075
-7.000 -0.2938 0.01191 0.00550 -0.0950 0.6945 0.0077
-6.750 -0.2687 0.01164 0.00519 -0.0947 0.6936 0.0082
-6.500 -0.2433 0.01135 0.00487 -0.0944 0.6928 0.0086
-6.250 -0.2178 0.01109 0.00458 -0.0941 0.6919 0.0090
-6.000 -0.1917 0.01088 0.00434 -0.0939 0.6909 0.0093
-5.750 -0.1666 0.01056 0.00401 -0.0936 0.6898 0.0105
-5.500 -0.1407 0.01035 0.00378 -0.0934 0.6888 0.0116
-5.250 -0.1144 0.01016 0.00357 -0.0932 0.6878 0.0124
-5.000 -0.0885 0.00994 0.00334 -0.0930 0.6868 0.0140
-4.750 -0.0623 0.00974 0.00314 -0.0928 0.6857 0.0161
-4.500 -0.0360 0.00955 0.00294 -0.0927 0.6846 0.0191
-4.250 -0.0097 0.00937 0.00277 -0.0925 0.6835 0.0237
-4.000 0.0164 0.00918 0.00262 -0.0924 0.6825 0.0319
-3.750 0.0426 0.00901 0.00248 -0.0922 0.6814 0.0423
-3.500 0.0690 0.00886 0.00235 -0.0921 0.6803 0.0527
-3.250 0.0954 0.00871 0.00224 -0.0920 0.6791 0.0653
-3.000 0.1220 0.00857 0.00214 -0.0919 0.6782 0.0778
-2.750 0.1483 0.00840 0.00205 -0.0918 0.6771 0.0987
-2.500 0.1745 0.00823 0.00197 -0.0916 0.6758 0.1224
-2.250 0.2005 0.00805 0.00190 -0.0915 0.6745 0.1530
-2.000 0.2265 0.00788 0.00182 -0.0913 0.6732 0.1853
-1.750 0.2527 0.00773 0.00176 -0.0911 0.6718 0.2143
-1.500 0.2789 0.00758 0.00170 -0.0910 0.6702 0.2461
-1.250 0.3042 0.00739 0.00164 -0.0907 0.6689 0.2951
-1.000 0.3276 0.00709 0.00159 -0.0901 0.6674 0.3770
-0.750 0.3508 0.00682 0.00154 -0.0894 0.6660 0.4575
-0.500 0.3735 0.00656 0.00152 -0.0885 0.6645 0.5378
-0.250 0.3950 0.00627 0.00150 -0.0874 0.6629 0.6240
0.000 0.4178 0.00608 0.00150 -0.0864 0.6611 0.6848
0.250 0.4398 0.00592 0.00157 -0.0852 0.6591 0.7543
0.500 0.4655 0.00590 0.00162 -0.0848 0.6571 0.7843
0.750 0.4923 0.00592 0.00165 -0.0846 0.6553 0.8004
1.000 0.5191 0.00594 0.00166 -0.0845 0.6534 0.8133
1.250 0.5460 0.00597 0.00169 -0.0844 0.6512 0.8218
1.500 0.5729 0.00600 0.00175 -0.0843 0.6491 0.8317
1.750 0.5989 0.00604 0.00181 -0.0840 0.6466 0.8432
2.000 0.6259 0.00606 0.00186 -0.0839 0.6440 0.8498
2.250 0.6526 0.00609 0.00190 -0.0837 0.6412 0.8552
2.500 0.6793 0.00613 0.00192 -0.0836 0.6387 0.8593
2.750 0.7065 0.00615 0.00196 -0.0836 0.6363 0.8629
3.000 0.7336 0.00618 0.00203 -0.0836 0.6333 0.8667
3.250 0.7604 0.00621 0.00208 -0.0836 0.6292 0.8700
3.500 0.7870 0.00625 0.00212 -0.0835 0.6257 0.8725
3.750 0.8136 0.00629 0.00216 -0.0834 0.6216 0.8744
4.000 0.8410 0.00631 0.00223 -0.0835 0.6171 0.8762
4.250 0.8674 0.00636 0.00228 -0.0834 0.6110 0.8779
4.500 0.8939 0.00641 0.00235 -0.0834 0.6060 0.8795
4.750 0.9198 0.00647 0.00243 -0.0832 0.5981 0.8813
5.000 0.9450 0.00656 0.00251 -0.0829 0.5901 0.8832
5.250 0.9690 0.00667 0.00261 -0.0823 0.5794 0.8850
5.500 0.9916 0.00683 0.00274 -0.0815 0.5641 0.8869
5.750 1.0055 0.00725 0.00300 -0.0790 0.5251 0.8895
6.000 1.0184 0.00776 0.00336 -0.0764 0.4875 0.8923
6.250 1.0183 0.00873 0.00402 -0.0716 0.4224 0.8962
6.500 1.0184 0.00970 0.00474 -0.0671 0.3676 0.9007
6.750 1.0247 0.01095 0.00572 -0.0646 0.3103 0.9051
7.000 1.0405 0.01226 0.00683 -0.0646 0.2628 0.9092
7.250 1.0568 0.01387 0.00824 -0.0655 0.2157 0.9136
7.750 1.0824 0.01768 0.01154 -0.0666 0.1104 0.9241
8.000 1.0935 0.01930 0.01298 -0.0663 0.0704 0.9318
8.250 1.1113 0.02049 0.01411 -0.0666 0.0496 0.9421
8.500 1.1334 0.02153 0.01512 -0.0676 0.0357 0.9570
9.000 1.1687 0.02358 0.01712 -0.0672 0.0228 1.0000
9.250 1.1832 0.02451 0.01805 -0.0664 0.0200 1.0000
9.500 1.1974 0.02548 0.01902 -0.0656 0.0175 1.0000
9.750 1.2129 0.02633 0.01991 -0.0648 0.0167 1.0000
10.000 1.2273 0.02727 0.02087 -0.0640 0.0155 1.0000
10.250 1.2392 0.02840 0.02199 -0.0630 0.0133 1.0000
10.500 1.2532 0.02937 0.02299 -0.0621 0.0131 1.0000
10.750 1.2679 0.03029 0.02395 -0.0614 0.0123 1.0000
11.000 1.2808 0.03135 0.02505 -0.0605 0.0117 1.0000
11.250 1.2935 0.03245 0.02618 -0.0597 0.0110 1.0000
11.500 1.3049 0.03369 0.02741 -0.0588 0.0094 1.0000
11.750 1.3169 0.03491 0.02868 -0.0579 0.0095 1.0000
12.000 1.3296 0.03607 0.02988 -0.0572 0.0090 1.0000
12.250 1.3426 0.03723 0.03108 -0.0565 0.0085 1.0000
12.500 1.3541 0.03854 0.03242 -0.0558 0.0080 1.0000
12.750 1.3646 0.03996 0.03389 -0.0549 0.0077 1.0000
13.000 1.3752 0.04135 0.03531 -0.0542 0.0073 1.0000
13.250 1.3844 0.04290 0.03690 -0.0534 0.0069 1.0000
13.500 1.3945 0.04440 0.03845 -0.0526 0.0067 1.0000
13.750 1.4049 0.04590 0.04001 -0.0520 0.0064 1.0000
14.000 1.4130 0.04763 0.04180 -0.0513 0.0063 1.0000
14.250 1.4232 0.04916 0.04337 -0.0507 0.0059 1.0000
14.500 1.4319 0.05086 0.04512 -0.0501 0.0057 1.0000
14.750 1.4392 0.05272 0.04705 -0.0494 0.0056 1.0000
15.000 1.4467 0.05458 0.04895 -0.0489 0.0052 1.0000
15.250 1.4520 0.05672 0.05115 -0.0483 0.0051 1.0000
15.500 1.4579 0.05880 0.05330 -0.0477 0.0049 1.0000
15.750 1.4624 0.06107 0.05563 -0.0472 0.0047 1.0000
16.000 1.4696 0.06306 0.05769 -0.0469 0.0044 1.0000
16.250 1.4726 0.06557 0.06028 -0.0464 0.0045 1.0000
16.500 1.4790 0.06771 0.06248 -0.0462 0.0042 1.0000
16.750 1.4819 0.07031 0.06516 -0.0459 0.0043 1.0000
17.000 1.4845 0.07296 0.06790 -0.0457 0.0041 1.0000
17.250 1.4876 0.07556 0.07057 -0.0456 0.0039 1.0000
17.500 1.4897 0.07833 0.07343 -0.0455 0.0039 1.0000
17.750 1.4938 0.08086 0.07601 -0.0456 0.0036 1.0000
18.000 1.4914 0.08432 0.07959 -0.0456 0.0037 1.0000
18.250 1.4918 0.08743 0.08276 -0.0459 0.0036 1.0000
18.500 1.4946 0.09023 0.08561 -0.0462 0.0033 1.0000
18.750 1.4922 0.09378 0.08926 -0.0466 0.0033 1.0000
19.000 1.4883 0.09758 0.09316 -0.0471 0.0033 1.0000
19.250 1.4818 0.10183 0.09750 -0.0478 0.0031 1.0000
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Polar data table (+)
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