AH 81-K-144/17 (ah81k144-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 81-K-144/17 (ah81k144-il) Reynolds number: 1,000,000 Max Cl/Cd: 156.14 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah81k144-il-1000000.txt Download as CSV file: xf-ah81k144-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2173 0.11201 0.10908 -0.0816 0.7394 0.0123
-12.250 -0.2090 0.10911 0.10617 -0.0834 0.7387 0.0126
-12.000 -0.3901 0.06194 0.05911 -0.1058 0.7393 0.0092
-11.750 -0.3586 0.06447 0.06167 -0.1050 0.7383 0.0093
-11.500 -0.3365 0.06456 0.06177 -0.1059 0.7372 0.0094
-11.250 -0.4641 0.03416 0.03049 -0.1299 0.7359 0.0085
-10.750 -0.4913 0.02895 0.02481 -0.1244 0.7335 0.0086
-10.500 -0.5106 0.02598 0.02152 -0.1191 0.7323 0.0087
-10.250 -0.5082 0.02415 0.01947 -0.1163 0.7310 0.0088
-10.000 -0.4997 0.02281 0.01801 -0.1142 0.7295 0.0092
-9.750 -0.4879 0.02159 0.01666 -0.1122 0.7288 0.0093
-9.500 -0.4762 0.02013 0.01500 -0.1101 0.7278 0.0092
-9.250 -0.4607 0.01904 0.01376 -0.1085 0.7268 0.0093
-9.000 -0.4411 0.01847 0.01312 -0.1075 0.7259 0.0096
-8.750 -0.4210 0.01785 0.01242 -0.1066 0.7248 0.0098
-8.500 -0.4010 0.01711 0.01158 -0.1055 0.7238 0.0102
-8.250 -0.3811 0.01631 0.01066 -0.1044 0.7228 0.0103
-8.000 -0.3589 0.01579 0.01007 -0.1036 0.7218 0.0106
-7.750 -0.3373 0.01514 0.00932 -0.1028 0.7207 0.0109
-7.500 -0.3153 0.01456 0.00865 -0.1020 0.7196 0.0110
-7.250 -0.2920 0.01410 0.00810 -0.1013 0.7186 0.0113
-7.000 -0.2686 0.01367 0.00760 -0.1006 0.7176 0.0115
-6.750 -0.2493 0.01283 0.00667 -0.0994 0.7166 0.0123
-6.500 -0.2260 0.01246 0.00626 -0.0988 0.7153 0.0130
-6.250 -0.2019 0.01214 0.00591 -0.0982 0.7144 0.0138
-6.000 -0.1774 0.01183 0.00557 -0.0977 0.7136 0.0144
-5.750 -0.1526 0.01154 0.00525 -0.0973 0.7126 0.0150
-5.500 -0.1296 0.01108 0.00474 -0.0965 0.7115 0.0163
-5.250 -0.1047 0.01081 0.00446 -0.0961 0.7105 0.0180
-5.000 -0.0791 0.01060 0.00422 -0.0957 0.7094 0.0195
-4.750 -0.0546 0.01028 0.00391 -0.0952 0.7083 0.0241
-4.500 -0.0293 0.01003 0.00368 -0.0948 0.7071 0.0317
-4.250 -0.0042 0.00977 0.00348 -0.0945 0.7060 0.0449
-4.000 0.0215 0.00956 0.00332 -0.0942 0.7050 0.0583
-3.750 0.0474 0.00938 0.00318 -0.0940 0.7040 0.0739
-3.500 0.0731 0.00919 0.00305 -0.0938 0.7029 0.0953
-3.250 0.0989 0.00903 0.00295 -0.0936 0.7017 0.1190
-3.000 0.1242 0.00891 0.00293 -0.0933 0.7002 0.1503
-2.750 0.1491 0.00870 0.00284 -0.0929 0.6994 0.1845
-2.500 0.1731 0.00843 0.00276 -0.0924 0.6984 0.2350
-2.250 0.1965 0.00814 0.00268 -0.0917 0.6971 0.2989
-2.000 0.2188 0.00781 0.00261 -0.0909 0.6957 0.3796
-1.750 0.2406 0.00748 0.00254 -0.0899 0.6944 0.4654
-1.500 0.2598 0.00706 0.00247 -0.0883 0.6929 0.5761
-1.250 0.2773 0.00667 0.00243 -0.0862 0.6915 0.6872
-1.000 0.2980 0.00650 0.00249 -0.0846 0.6902 0.7684
-0.750 0.3234 0.00650 0.00252 -0.0840 0.6889 0.8025
-0.500 0.3501 0.00655 0.00255 -0.0838 0.6875 0.8182
-0.250 0.3772 0.00665 0.00263 -0.0837 0.6857 0.8283
0.000 0.4032 0.00667 0.00266 -0.0833 0.6846 0.8372
0.250 0.4294 0.00669 0.00270 -0.0830 0.6831 0.8452
0.500 0.4556 0.00671 0.00272 -0.0827 0.6814 0.8525
0.750 0.4828 0.00671 0.00273 -0.0826 0.6795 0.8579
1.000 0.5093 0.00672 0.00273 -0.0824 0.6778 0.8638
1.250 0.5369 0.00671 0.00272 -0.0824 0.6760 0.8696
1.500 0.5636 0.00673 0.00273 -0.0821 0.6743 0.8769
1.750 0.5905 0.00675 0.00275 -0.0820 0.6724 0.8840
2.000 0.6165 0.00680 0.00283 -0.0816 0.6706 0.8911
2.250 0.6416 0.00679 0.00285 -0.0811 0.6686 0.8957
2.500 0.6688 0.00677 0.00286 -0.0811 0.6665 0.8993
2.750 0.6958 0.00675 0.00286 -0.0811 0.6642 0.9034
3.000 0.7223 0.00673 0.00285 -0.0809 0.6619 0.9072
3.250 0.7491 0.00671 0.00282 -0.0808 0.6596 0.9102
3.500 0.7778 0.00673 0.00283 -0.0812 0.6571 0.9128
3.750 0.8038 0.00670 0.00287 -0.0810 0.6543 0.9155
4.000 0.8304 0.00668 0.00289 -0.0809 0.6512 0.9180
4.250 0.8572 0.00666 0.00288 -0.0809 0.6480 0.9203
4.500 0.8841 0.00665 0.00287 -0.0809 0.6449 0.9225
4.750 0.9104 0.00667 0.00292 -0.0808 0.6415 0.9247
5.000 0.9380 0.00664 0.00296 -0.0810 0.6371 0.9270
5.250 0.9658 0.00664 0.00299 -0.0812 0.6329 0.9291
5.500 0.9919 0.00662 0.00300 -0.0811 0.6253 0.9317
5.750 1.0164 0.00661 0.00299 -0.0806 0.6127 0.9348
6.000 1.0399 0.00666 0.00303 -0.0799 0.5966 0.9378
6.250 1.0629 0.00687 0.00315 -0.0793 0.5658 0.9412
6.500 1.0875 0.00718 0.00339 -0.0792 0.5385 0.9447
6.750 1.1107 0.00764 0.00373 -0.0790 0.5057 0.9493
7.000 1.1341 0.00831 0.00425 -0.0791 0.4646 0.9543
7.250 1.1580 0.00949 0.00514 -0.0801 0.3996 0.9599
7.500 1.1767 0.01100 0.00630 -0.0807 0.3266 0.9700
7.750 1.1800 0.01289 0.00786 -0.0789 0.2621 1.0000
8.000 1.1779 0.01499 0.00971 -0.0766 0.2113 1.0000
8.250 1.1726 0.01734 0.01174 -0.0740 0.1543 1.0000
8.500 1.1707 0.01937 0.01351 -0.0715 0.1088 1.0000
8.750 1.1707 0.02123 0.01515 -0.0692 0.0705 1.0000
9.000 1.1756 0.02278 0.01655 -0.0674 0.0453 1.0000
9.250 1.1845 0.02408 0.01778 -0.0659 0.0328 1.0000
9.500 1.1960 0.02519 0.01888 -0.0647 0.0265 1.0000
9.750 1.2075 0.02633 0.01999 -0.0636 0.0229 1.0000
10.000 1.2207 0.02734 0.02104 -0.0626 0.0208 1.0000
10.250 1.2331 0.02841 0.02214 -0.0615 0.0195 1.0000
10.500 1.2418 0.02976 0.02350 -0.0602 0.0170 1.0000
10.750 1.2536 0.03090 0.02469 -0.0591 0.0163 1.0000
11.000 1.2668 0.03193 0.02576 -0.0583 0.0155 1.0000
11.250 1.2787 0.03311 0.02698 -0.0574 0.0148 1.0000
11.500 1.2893 0.03443 0.02832 -0.0564 0.0139 1.0000
11.750 1.2949 0.03618 0.03012 -0.0550 0.0128 1.0000
12.000 1.3025 0.03779 0.03181 -0.0538 0.0123 1.0000
12.250 1.3163 0.03890 0.03296 -0.0532 0.0118 1.0000
12.500 1.3270 0.04031 0.03441 -0.0524 0.0111 1.0000
12.750 1.3374 0.04175 0.03589 -0.0516 0.0106 1.0000
13.000 1.3477 0.04322 0.03740 -0.0509 0.0104 1.0000
13.250 1.3546 0.04500 0.03922 -0.0500 0.0100 1.0000
13.500 1.3493 0.04796 0.04229 -0.0483 0.0093 1.0000
13.750 1.3611 0.04939 0.04376 -0.0478 0.0091 1.0000
14.000 1.3716 0.05093 0.04537 -0.0473 0.0088 1.0000
14.250 1.3793 0.05276 0.04726 -0.0466 0.0085 1.0000
14.500 1.3823 0.05509 0.04967 -0.0458 0.0085 1.0000
14.750 1.3880 0.05718 0.05183 -0.0451 0.0082 1.0000
15.000 1.3982 0.05886 0.05355 -0.0448 0.0079 1.0000
15.250 1.4019 0.06123 0.05598 -0.0442 0.0077 1.0000
15.500 1.4096 0.06320 0.05799 -0.0440 0.0074 1.0000
15.750 1.4102 0.06595 0.06082 -0.0434 0.0073 1.0000
16.000 1.4071 0.06915 0.06409 -0.0428 0.0069 1.0000
16.250 1.4009 0.07277 0.06783 -0.0421 0.0067 1.0000
16.500 1.4049 0.07531 0.07046 -0.0419 0.0066 1.0000
16.750 1.4096 0.07781 0.07303 -0.0420 0.0065 1.0000
17.000 1.4098 0.08083 0.07615 -0.0418 0.0065 1.0000
17.250 1.4120 0.08368 0.07910 -0.0419 0.0063 1.0000
17.500 1.4133 0.08673 0.08224 -0.0421 0.0061 1.0000
17.750 1.4137 0.08991 0.08550 -0.0423 0.0061 1.0000
18.000 1.4177 0.09272 0.08839 -0.0428 0.0057 1.0000
18.250 1.4126 0.09664 0.09242 -0.0431 0.0058 1.0000
18.500 1.4128 0.10000 0.09586 -0.0438 0.0056 1.0000
18.750 1.4109 0.10364 0.09959 -0.0444 0.0055 1.0000
19.000 1.4092 0.10737 0.10340 -0.0453 0.0054 1.0000
19.250 1.4074 0.11118 0.10729 -0.0464 0.0052 1.0000
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