AH 82-150 F (ah82150f-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 82-150 F (ah82150f-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.8 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah82150f-il-1000000-n5.txt Download as CSV file: xf-ah82150f-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 F
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6033 0.04625 0.04317 -0.1350 0.7844 0.0042
-14.250 -0.6098 0.04260 0.03942 -0.1370 0.7835 0.0043
-14.000 -0.6567 0.03616 0.03270 -0.1369 0.7823 0.0042
-13.750 -0.6604 0.03413 0.03056 -0.1358 0.7813 0.0042
-13.500 -0.6792 0.03115 0.02736 -0.1330 0.7802 0.0042
-13.250 -0.6812 0.02948 0.02556 -0.1309 0.7793 0.0043
-13.000 -0.6789 0.02812 0.02407 -0.1288 0.7784 0.0044
-12.750 -0.6786 0.02667 0.02245 -0.1263 0.7774 0.0044
-12.500 -0.6757 0.02539 0.02102 -0.1239 0.7764 0.0044
-12.250 -0.6671 0.02447 0.01999 -0.1219 0.7757 0.0045
-12.000 -0.6592 0.02349 0.01890 -0.1197 0.7751 0.0046
-11.750 -0.6538 0.02235 0.01761 -0.1170 0.7743 0.0046
-11.500 -0.6457 0.02140 0.01655 -0.1145 0.7735 0.0046
-11.250 -0.6349 0.02070 0.01574 -0.1122 0.7726 0.0047
-11.000 -0.6250 0.01980 0.01471 -0.1098 0.7718 0.0047
-10.750 -0.6151 0.01857 0.01330 -0.1075 0.7711 0.0049
-10.500 -0.5991 0.01778 0.01239 -0.1060 0.7704 0.0051
-10.250 -0.5816 0.01704 0.01156 -0.1048 0.7697 0.0054
-10.000 -0.5619 0.01647 0.01090 -0.1039 0.7690 0.0056
-9.750 -0.5409 0.01600 0.01036 -0.1031 0.7684 0.0058
-9.500 -0.5196 0.01553 0.00983 -0.1024 0.7678 0.0060
-9.250 -0.4972 0.01515 0.00939 -0.1019 0.7672 0.0063
-9.000 -0.4752 0.01470 0.00887 -0.1013 0.7666 0.0065
-8.750 -0.4530 0.01424 0.00833 -0.1007 0.7660 0.0068
-8.500 -0.4301 0.01385 0.00788 -0.1002 0.7654 0.0070
-8.250 -0.4070 0.01347 0.00743 -0.0997 0.7648 0.0072
-8.000 -0.3833 0.01314 0.00702 -0.0993 0.7643 0.0073
-7.750 -0.3606 0.01269 0.00650 -0.0987 0.7637 0.0077
-7.500 -0.3373 0.01229 0.00605 -0.0982 0.7630 0.0083
-7.250 -0.3130 0.01201 0.00573 -0.0979 0.7622 0.0088
-7.000 -0.2886 0.01172 0.00543 -0.0976 0.7617 0.0095
-6.750 -0.2638 0.01146 0.00514 -0.0974 0.7612 0.0102
-6.500 -0.2387 0.01123 0.00489 -0.0972 0.7607 0.0109
-6.250 -0.2140 0.01096 0.00460 -0.0969 0.7602 0.0128
-6.000 -0.1887 0.01075 0.00440 -0.0968 0.7597 0.0147
-5.750 -0.1629 0.01057 0.00421 -0.0967 0.7592 0.0160
-5.500 -0.1375 0.01036 0.00400 -0.0966 0.7586 0.0185
-5.250 -0.1117 0.01018 0.00383 -0.0965 0.7580 0.0207
-5.000 -0.0854 0.01004 0.00367 -0.0965 0.7574 0.0225
-4.750 -0.0593 0.00988 0.00350 -0.0965 0.7569 0.0245
-4.500 -0.0332 0.00972 0.00335 -0.0965 0.7562 0.0276
-4.250 -0.0067 0.00959 0.00324 -0.0965 0.7555 0.0313
-4.000 0.0199 0.00947 0.00310 -0.0966 0.7548 0.0338
-3.750 0.0464 0.00932 0.00296 -0.0966 0.7541 0.0384
-3.500 0.0731 0.00920 0.00285 -0.0967 0.7536 0.0428
-3.250 0.0999 0.00909 0.00274 -0.0969 0.7530 0.0482
-3.000 0.1267 0.00897 0.00265 -0.0970 0.7524 0.0554
-2.750 0.1534 0.00883 0.00255 -0.0971 0.7518 0.0678
-2.500 0.1795 0.00865 0.00246 -0.0971 0.7511 0.0949
-2.250 0.2050 0.00842 0.00237 -0.0970 0.7504 0.1382
-2.000 0.2299 0.00815 0.00229 -0.0969 0.7497 0.2000
-1.750 0.2541 0.00783 0.00221 -0.0967 0.7486 0.2828
-1.500 0.2776 0.00747 0.00214 -0.0963 0.7471 0.3665
-1.250 0.3018 0.00715 0.00206 -0.0960 0.7451 0.4391
-1.000 0.3247 0.00669 0.00195 -0.0955 0.7429 0.5484
-0.750 0.3414 0.00597 0.00206 -0.0935 0.7407 0.7977
-0.500 0.3695 0.00607 0.00217 -0.0937 0.7386 0.8223
-0.250 0.3982 0.00612 0.00218 -0.0940 0.7364 0.8296
0.000 0.4272 0.00616 0.00216 -0.0945 0.7345 0.8332
0.250 0.4550 0.00619 0.00223 -0.0947 0.7326 0.8363
0.500 0.4829 0.00625 0.00230 -0.0949 0.7307 0.8400
0.750 0.5111 0.00634 0.00239 -0.0952 0.7286 0.8466
1.000 0.5380 0.00642 0.00250 -0.0951 0.7264 0.8512
1.250 0.5661 0.00645 0.00253 -0.0953 0.7243 0.8534
1.500 0.5948 0.00644 0.00251 -0.0958 0.7223 0.8541
1.750 0.6233 0.00644 0.00251 -0.0963 0.7201 0.8546
2.000 0.6515 0.00643 0.00253 -0.0967 0.7172 0.8552
2.250 0.6797 0.00643 0.00253 -0.0971 0.7139 0.8557
2.500 0.7079 0.00642 0.00253 -0.0975 0.7105 0.8563
2.750 0.7360 0.00641 0.00252 -0.0979 0.7072 0.8568
3.000 0.7638 0.00642 0.00257 -0.0983 0.7025 0.8575
3.250 0.7912 0.00642 0.00257 -0.0985 0.6967 0.8581
3.500 0.8185 0.00643 0.00260 -0.0987 0.6897 0.8586
3.750 0.8448 0.00645 0.00261 -0.0987 0.6802 0.8591
4.000 0.8697 0.00650 0.00264 -0.0984 0.6651 0.8596
4.250 0.8798 0.00687 0.00275 -0.0950 0.6144 0.8604
4.500 0.8875 0.00733 0.00304 -0.0912 0.5747 0.8613
4.750 0.8958 0.00772 0.00331 -0.0876 0.5454 0.8622
5.000 0.8937 0.00815 0.00362 -0.0818 0.5147 0.8634
5.250 0.8888 0.00880 0.00412 -0.0757 0.4795 0.8649
5.500 0.8860 0.00953 0.00471 -0.0704 0.4465 0.8664
5.750 0.8877 0.01026 0.00532 -0.0661 0.4170 0.8676
6.000 0.8913 0.01102 0.00596 -0.0623 0.3875 0.8687
6.250 0.8910 0.01200 0.00675 -0.0581 0.3467 0.8700
6.500 0.8879 0.01316 0.00765 -0.0536 0.2943 0.8712
6.750 0.8847 0.01442 0.00859 -0.0492 0.2339 0.8724
7.000 0.8782 0.01591 0.00968 -0.0445 0.1591 0.8735
7.250 0.8714 0.01754 0.01087 -0.0400 0.0753 0.8744
7.500 0.8716 0.01892 0.01194 -0.0365 0.0132 0.8753
7.750 0.8890 0.01942 0.01245 -0.0355 0.0109 0.8761
8.000 0.9055 0.01998 0.01302 -0.0344 0.0087 0.8769
8.250 0.9232 0.02049 0.01356 -0.0335 0.0078 0.8775
8.500 0.9404 0.02102 0.01413 -0.0325 0.0073 0.8782
8.750 0.9570 0.02160 0.01474 -0.0315 0.0068 0.8788
9.000 0.9725 0.02226 0.01543 -0.0303 0.0062 0.8795
9.250 0.9873 0.02298 0.01618 -0.0291 0.0055 0.8802
9.500 1.0014 0.02375 0.01701 -0.0279 0.0053 0.8809
9.750 1.0183 0.02436 0.01764 -0.0270 0.0050 0.8816
10.000 1.0333 0.02510 0.01842 -0.0260 0.0048 0.8823
10.250 1.0474 0.02591 0.01929 -0.0248 0.0046 0.8830
10.500 1.0627 0.02665 0.02006 -0.0239 0.0043 0.8838
10.750 1.0765 0.02751 0.02096 -0.0228 0.0041 0.8845
11.000 1.0910 0.02833 0.02182 -0.0219 0.0038 0.8853
11.250 1.1030 0.02935 0.02288 -0.0207 0.0036 0.8860
11.500 1.1135 0.03049 0.02406 -0.0194 0.0033 0.8868
11.750 1.1224 0.03178 0.02542 -0.0180 0.0032 0.8875
12.000 1.1301 0.03321 0.02692 -0.0165 0.0031 0.8882
12.500 1.1552 0.03534 0.02918 -0.0147 0.0029 0.8897
12.750 1.1640 0.03674 0.03065 -0.0136 0.0029 0.8906
13.000 1.1711 0.03830 0.03230 -0.0124 0.0028 0.8915
13.250 1.1785 0.03990 0.03398 -0.0112 0.0027 0.8925
13.500 1.1915 0.04102 0.03515 -0.0106 0.0025 0.8936
13.750 1.1960 0.04293 0.03716 -0.0094 0.0025 0.8947
14.000 1.2053 0.04445 0.03875 -0.0087 0.0023 0.8958
14.250 1.2087 0.04660 0.04099 -0.0077 0.0024 0.8969
14.500 1.2159 0.04842 0.04289 -0.0070 0.0023 0.8979
14.750 1.2234 0.05025 0.04481 -0.0065 0.0022 0.8989
15.000 1.2289 0.05233 0.04697 -0.0059 0.0021 0.9000
15.250 1.2350 0.05440 0.04913 -0.0055 0.0021 0.9010
15.500 1.2375 0.05693 0.05176 -0.0050 0.0021 0.9019
16.000 1.2492 0.06139 0.05637 -0.0047 0.0019 0.9042
16.250 1.2511 0.06412 0.05921 -0.0046 0.0019 0.9054
16.500 1.2550 0.06671 0.06188 -0.0047 0.0018 0.9068
16.750 1.2515 0.07027 0.06560 -0.0047 0.0019 0.9080
17.000 1.2543 0.07315 0.06857 -0.0051 0.0018 0.9095
17.250 1.2532 0.07660 0.07215 -0.0055 0.0019 0.9109
17.500 1.2516 0.08021 0.07587 -0.0061 0.0018 0.9123
17.750 1.2483 0.08414 0.07992 -0.0069 0.0018 0.9137
18.000 1.2446 0.08825 0.08416 -0.0080 0.0017 0.9150
18.500 1.2366 0.09680 0.09300 -0.0105 0.0017 0.9182
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