FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-163 AIRFOIL (fx61163-il) Reynolds number: 500,000 Max Cl/Cd: 103.07 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61163-il-500000.txt Download as CSV file: xf-fx61163-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-163 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3976 0.12666 0.12434 -0.0356 1.0001 0.0176
-12.500 -0.4006 0.11920 0.11690 -0.0400 1.0001 0.0185
-9.250 -0.4341 0.02883 0.02527 -0.0935 0.8215 0.0218
-9.000 -0.4323 0.02634 0.02244 -0.0929 0.7920 0.0226
-8.250 -0.4388 0.02514 0.01920 -0.0912 0.7723 0.0143
-8.000 -0.4153 0.02452 0.01833 -0.0908 0.7551 0.0140
-7.750 -0.3932 0.02229 0.01593 -0.0899 0.7424 0.0137
-7.500 -0.3702 0.02088 0.01431 -0.0892 0.7315 0.0137
-7.250 -0.3466 0.01980 0.01307 -0.0885 0.7220 0.0137
-7.000 -0.3222 0.01897 0.01211 -0.0881 0.7132 0.0139
-6.750 -0.3019 0.01748 0.01053 -0.0868 0.7060 0.0144
-6.500 -0.2792 0.01659 0.00962 -0.0864 0.6988 0.0151
-6.250 -0.2554 0.01586 0.00880 -0.0863 0.6928 0.0153
-6.000 -0.2306 0.01514 0.00802 -0.0864 0.6872 0.0156
-5.750 -0.2047 0.01448 0.00731 -0.0868 0.6817 0.0161
-5.500 -0.1778 0.01393 0.00665 -0.0873 0.6769 0.0168
-5.250 -0.1499 0.01341 0.00607 -0.0880 0.6720 0.0179
-5.000 -0.1215 0.01289 0.00546 -0.0887 0.6673 0.0194
-4.750 -0.0924 0.01243 0.00494 -0.0895 0.6631 0.0232
-4.500 -0.0615 0.01130 0.00420 -0.0916 0.6591 0.1138
-4.250 -0.0201 0.00879 0.00316 -0.0981 0.6546 0.4826
-4.000 0.0117 0.00861 0.00315 -0.0992 0.6506 0.5476
-3.750 0.0422 0.00872 0.00324 -0.0998 0.6469 0.5844
-3.500 0.0723 0.00899 0.00349 -0.1001 0.6433 0.6129
-3.250 0.1014 0.00928 0.00376 -0.1001 0.6395 0.6282
-3.000 0.1292 0.00956 0.00403 -0.0998 0.6360 0.6371
-2.750 0.1589 0.00973 0.00410 -0.1001 0.6328 0.6439
-2.500 0.1875 0.00987 0.00421 -0.1002 0.6296 0.6474
-2.250 0.2169 0.00991 0.00422 -0.1005 0.6260 0.6509
-2.000 0.2472 0.00996 0.00419 -0.1012 0.6222 0.6555
-1.750 0.2762 0.01003 0.00420 -0.1014 0.6186 0.6589
-1.500 0.3049 0.01016 0.00428 -0.1016 0.6151 0.6616
-1.250 0.3339 0.01020 0.00432 -0.1018 0.6118 0.6646
-1.000 0.3637 0.01026 0.00435 -0.1023 0.6085 0.6685
-0.750 0.3942 0.01030 0.00432 -0.1031 0.6053 0.6722
-0.500 0.4227 0.01036 0.00436 -0.1032 0.6022 0.6743
-0.250 0.4516 0.01045 0.00443 -0.1035 0.5990 0.6765
0.000 0.4805 0.01048 0.00448 -0.1038 0.5957 0.6790
0.250 0.5100 0.01051 0.00450 -0.1042 0.5920 0.6819
0.500 0.5400 0.01056 0.00449 -0.1049 0.5883 0.6852
0.750 0.5698 0.01062 0.00450 -0.1054 0.5846 0.6876
1.000 0.5980 0.01062 0.00455 -0.1056 0.5809 0.6894
1.250 0.6266 0.01066 0.00461 -0.1058 0.5773 0.6915
1.500 0.6556 0.01071 0.00466 -0.1061 0.5739 0.6939
1.750 0.6851 0.01082 0.00473 -0.1066 0.5704 0.6965
2.000 0.7144 0.01083 0.00477 -0.1071 0.5665 0.6993
2.250 0.7441 0.01085 0.00480 -0.1076 0.5624 0.7018
2.500 0.7724 0.01087 0.00484 -0.1078 0.5587 0.7036
2.750 0.8008 0.01094 0.00492 -0.1081 0.5545 0.7054
3.000 0.8288 0.01094 0.00498 -0.1082 0.5492 0.7076
3.250 0.8574 0.01097 0.00504 -0.1085 0.5444 0.7099
3.500 0.8865 0.01107 0.00511 -0.1089 0.5404 0.7123
3.750 0.9153 0.01107 0.00518 -0.1093 0.5349 0.7145
4.000 0.9441 0.01109 0.00520 -0.1097 0.5289 0.7167
4.250 0.9716 0.01111 0.00527 -0.1097 0.5229 0.7185
4.500 0.9993 0.01113 0.00536 -0.1098 0.5167 0.7203
4.750 1.0267 0.01119 0.00543 -0.1099 0.5095 0.7222
5.000 1.0542 0.01119 0.00549 -0.1100 0.5000 0.7242
5.250 1.0818 0.01125 0.00558 -0.1101 0.4908 0.7264
5.500 1.1092 0.01135 0.00566 -0.1102 0.4815 0.7288
5.750 1.1370 0.01144 0.00579 -0.1104 0.4706 0.7309
6.000 1.1638 0.01152 0.00592 -0.1104 0.4608 0.7326
6.250 1.1899 0.01166 0.00609 -0.1103 0.4509 0.7344
6.500 1.2156 0.01183 0.00628 -0.1101 0.4388 0.7364
6.750 1.2409 0.01204 0.00650 -0.1098 0.4243 0.7384
7.000 1.2653 0.01231 0.00675 -0.1095 0.4052 0.7406
7.250 1.2885 0.01268 0.00705 -0.1089 0.3824 0.7429
7.500 1.3115 0.01309 0.00738 -0.1084 0.3597 0.7450
7.750 1.3325 0.01358 0.00780 -0.1076 0.3352 0.7467
8.000 1.3523 0.01411 0.00825 -0.1066 0.3072 0.7486
8.250 1.3699 0.01478 0.00880 -0.1052 0.2762 0.7505
8.500 1.3859 0.01555 0.00943 -0.1036 0.2421 0.7525
8.750 1.4001 0.01642 0.01014 -0.1018 0.2106 0.7545
9.000 1.4108 0.01743 0.01098 -0.0996 0.1789 0.7566
9.250 1.4208 0.01837 0.01182 -0.0971 0.1531 0.7588
9.500 1.4267 0.01935 0.01268 -0.0940 0.1308 0.7609
9.750 1.4314 0.02051 0.01375 -0.0911 0.1084 0.7630
10.000 1.4362 0.02172 0.01489 -0.0883 0.0896 0.7649
10.250 1.4403 0.02305 0.01618 -0.0858 0.0737 0.7670
10.500 1.4429 0.02462 0.01770 -0.0834 0.0611 0.7692
10.750 1.4476 0.02620 0.01930 -0.0817 0.0523 0.7715
11.000 1.4527 0.02794 0.02105 -0.0804 0.0432 0.7739
11.250 1.4528 0.03022 0.02330 -0.0791 0.0328 0.7762
11.500 1.4546 0.03247 0.02558 -0.0781 0.0266 0.7784
11.750 1.4561 0.03485 0.02803 -0.0772 0.0218 0.7806
12.000 1.4568 0.03740 0.03063 -0.0765 0.0178 0.7829
12.250 1.4574 0.04001 0.03330 -0.0758 0.0140 0.7852
12.500 1.4550 0.04293 0.03628 -0.0752 0.0107 0.7876
13.000 1.4521 0.04868 0.04218 -0.0740 0.0077 0.7922
13.250 1.4510 0.05152 0.04513 -0.0736 0.0070 0.7947
13.500 1.4482 0.05463 0.04833 -0.0732 0.0065 0.7975
13.750 1.4439 0.05799 0.05180 -0.0729 0.0061 0.8002
14.000 1.4410 0.06128 0.05520 -0.0727 0.0059 0.8030
14.250 1.4388 0.06459 0.05862 -0.0727 0.0058 0.8057
14.500 1.4357 0.06805 0.06222 -0.0728 0.0056 0.8084
14.750 1.4323 0.07162 0.06591 -0.0729 0.0055 0.8115
15.000 1.4281 0.07537 0.06978 -0.0732 0.0054 0.8148
15.250 1.4238 0.07923 0.07375 -0.0737 0.0052 0.8183
15.500 1.4193 0.08318 0.07784 -0.0742 0.0051 0.8217
15.750 1.4139 0.08728 0.08207 -0.0748 0.0050 0.8255
16.000 1.4084 0.09146 0.08638 -0.0756 0.0049 0.8299
16.250 1.4021 0.09587 0.09091 -0.0765 0.0048 0.8347
16.500 1.3962 0.10025 0.09541 -0.0776 0.0047 0.8401
16.750 1.3887 0.10494 0.10022 -0.0788 0.0046 0.8464
17.000 1.3805 0.10974 0.10516 -0.0801 0.0045 0.8534
17.250 1.3711 0.11484 0.11039 -0.0816 0.0044 0.8621
17.500 1.3630 0.11971 0.11542 -0.0831 0.0044 0.8738
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