FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il) Reynolds number: 500,000 Max Cl/Cd: 124.82 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx62k153-il-500000.txt Download as CSV file: xf-fx62k153-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 62-K-153/20 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1677 0.10529 0.10255 -0.1086 0.9056 0.0161
-11.750 -0.1719 0.09959 0.09684 -0.1107 0.8998 0.0163
-11.500 -0.1679 0.09645 0.09366 -0.1117 0.8944 0.0166
-11.250 -0.1628 0.09334 0.09050 -0.1130 0.8899 0.0168
-11.000 -0.1583 0.09006 0.08722 -0.1146 0.8855 0.0171
-10.750 -0.1548 0.08646 0.08362 -0.1164 0.8811 0.0173
-10.500 -0.1524 0.08249 0.07962 -0.1187 0.8771 0.0176
-10.250 -0.1516 0.07796 0.07508 -0.1215 0.8735 0.0179
-10.000 -0.1533 0.07249 0.06963 -0.1254 0.8698 0.0181
-9.750 -0.1648 0.06295 0.06007 -0.1342 0.8657 0.0179
-9.500 -0.1831 0.05532 0.05229 -0.1411 0.8615 0.0178
-9.250 -0.2573 0.03847 0.03475 -0.1489 0.8541 0.0125
-9.000 -0.2482 0.03565 0.03177 -0.1501 0.8509 0.0111
-8.750 -0.2655 0.02449 0.01941 -0.1509 0.8472 0.0095
-8.500 -0.2447 0.02278 0.01747 -0.1513 0.8450 0.0098
-8.250 -0.2231 0.02127 0.01575 -0.1514 0.8426 0.0102
-8.000 -0.2003 0.01984 0.01408 -0.1513 0.8401 0.0110
-7.750 -0.1751 0.01894 0.01293 -0.1514 0.8379 0.0119
-7.500 -0.1528 0.01744 0.01135 -0.1513 0.8358 0.0132
-7.250 -0.1260 0.01694 0.01079 -0.1517 0.8339 0.0148
-7.000 -0.1001 0.01618 0.00987 -0.1519 0.8320 0.0166
-6.750 -0.0739 0.01580 0.00953 -0.1524 0.8300 0.0187
-6.500 -0.0469 0.01562 0.00930 -0.1527 0.8280 0.0209
-6.250 -0.0223 0.01481 0.00847 -0.1528 0.8258 0.0233
-6.000 0.0048 0.01443 0.00808 -0.1533 0.8237 0.0254
-5.750 0.0326 0.01403 0.00764 -0.1538 0.8216 0.0274
-5.500 0.0612 0.01362 0.00715 -0.1544 0.8198 0.0285
-5.250 0.0909 0.01280 0.00626 -0.1558 0.8181 0.0312
-5.000 0.1213 0.01248 0.00591 -0.1570 0.8163 0.0349
-4.750 0.1504 0.01208 0.00549 -0.1578 0.8143 0.0407
-4.500 0.1809 0.01162 0.00511 -0.1591 0.8122 0.0598
-4.250 0.2135 0.01098 0.00475 -0.1612 0.8101 0.1334
-4.000 0.2621 0.00911 0.00413 -0.1687 0.8084 0.4827
-3.750 0.2955 0.00894 0.00422 -0.1702 0.8065 0.5785
-3.500 0.3262 0.00905 0.00431 -0.1709 0.8046 0.6136
-3.250 0.3560 0.00925 0.00447 -0.1712 0.8028 0.6336
-3.000 0.3856 0.00944 0.00460 -0.1717 0.8009 0.6457
-2.750 0.4125 0.00964 0.00481 -0.1714 0.7986 0.6561
-2.500 0.4377 0.00999 0.00520 -0.1706 0.7961 0.6685
-2.250 0.4631 0.01033 0.00555 -0.1697 0.7937 0.6789
-2.000 0.4916 0.01042 0.00560 -0.1699 0.7916 0.6827
-1.750 0.5226 0.01046 0.00557 -0.1708 0.7896 0.6869
-1.500 0.5536 0.01050 0.00554 -0.1717 0.7877 0.6903
-1.250 0.5808 0.01059 0.00563 -0.1716 0.7852 0.6925
-1.000 0.6077 0.01064 0.00570 -0.1716 0.7822 0.6950
-0.750 0.6361 0.01066 0.00572 -0.1719 0.7793 0.6978
-0.500 0.6662 0.01067 0.00568 -0.1726 0.7768 0.7011
-0.250 0.6984 0.01065 0.00559 -0.1738 0.7742 0.7045
0.000 0.7274 0.01067 0.00560 -0.1741 0.7714 0.7062
0.250 0.7533 0.01067 0.00565 -0.1739 0.7675 0.7082
0.500 0.7811 0.01069 0.00569 -0.1740 0.7643 0.7105
0.750 0.8105 0.01070 0.00569 -0.1745 0.7616 0.7130
1.000 0.8413 0.01070 0.00567 -0.1753 0.7592 0.7158
1.250 0.8725 0.01074 0.00568 -0.1763 0.7567 0.7188
1.500 0.8991 0.01074 0.00574 -0.1764 0.7531 0.7207
1.750 0.9266 0.01075 0.00580 -0.1765 0.7497 0.7223
2.000 0.9554 0.01075 0.00582 -0.1768 0.7467 0.7243
2.250 0.9856 0.01073 0.00578 -0.1775 0.7436 0.7264
2.500 1.0118 0.01069 0.00582 -0.1773 0.7381 0.7288
2.750 1.0407 0.01057 0.00570 -0.1776 0.7321 0.7312
3.000 1.0713 0.01052 0.00562 -0.1784 0.7275 0.7338
3.250 1.0969 0.01049 0.00568 -0.1781 0.7218 0.7357
3.500 1.1246 0.01042 0.00564 -0.1782 0.7163 0.7373
3.750 1.1508 0.01039 0.00567 -0.1780 0.7098 0.7391
4.000 1.1772 0.01033 0.00565 -0.1778 0.7019 0.7412
4.250 1.2027 0.01031 0.00568 -0.1775 0.6925 0.7436
4.500 1.2284 0.01028 0.00567 -0.1772 0.6810 0.7461
4.750 1.2534 0.01029 0.00567 -0.1767 0.6659 0.7483
5.000 1.2775 0.01034 0.00574 -0.1761 0.6515 0.7502
5.250 1.3007 0.01044 0.00587 -0.1753 0.6368 0.7520
5.500 1.3231 0.01060 0.00603 -0.1744 0.6201 0.7540
5.750 1.3430 0.01086 0.00623 -0.1730 0.5985 0.7560
6.000 1.3587 0.01126 0.00652 -0.1707 0.5657 0.7582
6.250 1.3708 0.01181 0.00692 -0.1679 0.5291 0.7605
6.500 1.3790 0.01246 0.00740 -0.1643 0.4923 0.7630
6.750 1.3813 0.01321 0.00798 -0.1597 0.4536 0.7651
7.000 1.3835 0.01418 0.00877 -0.1553 0.4110 0.7670
7.250 1.3827 0.01540 0.00975 -0.1507 0.3640 0.7690
7.500 1.3812 0.01679 0.01090 -0.1463 0.3137 0.7712
7.750 1.3802 0.01831 0.01218 -0.1423 0.2693 0.7734
8.000 1.3820 0.01982 0.01347 -0.1390 0.2302 0.7758
8.250 1.3869 0.02124 0.01472 -0.1363 0.1956 0.7781
8.750 1.3947 0.02425 0.01743 -0.1308 0.1326 0.7817
9.000 1.4010 0.02567 0.01874 -0.1285 0.1098 0.7836
9.250 1.4073 0.02713 0.02010 -0.1263 0.0913 0.7856
9.500 1.4163 0.02843 0.02138 -0.1244 0.0775 0.7879
9.750 1.4255 0.02975 0.02266 -0.1227 0.0663 0.7902
10.000 1.4361 0.03100 0.02390 -0.1212 0.0578 0.7924
10.250 1.4459 0.03226 0.02519 -0.1196 0.0504 0.7943
10.500 1.4539 0.03368 0.02660 -0.1178 0.0430 0.7962
10.750 1.4641 0.03495 0.02791 -0.1163 0.0376 0.7982
11.000 1.4727 0.03638 0.02936 -0.1147 0.0326 0.8004
11.250 1.4822 0.03776 0.03078 -0.1133 0.0288 0.8028
11.500 1.4902 0.03930 0.03235 -0.1118 0.0247 0.8052
11.750 1.4967 0.04101 0.03405 -0.1102 0.0196 0.8074
12.000 1.5020 0.04282 0.03589 -0.1086 0.0142 0.8095
12.250 1.5052 0.04486 0.03796 -0.1068 0.0100 0.8115
12.500 1.5096 0.04683 0.03998 -0.1052 0.0077 0.8137
12.750 1.5133 0.04895 0.04217 -0.1036 0.0066 0.8160
13.000 1.5191 0.05092 0.04424 -0.1024 0.0061 0.8184
13.250 1.5238 0.05304 0.04645 -0.1011 0.0056 0.8210
13.500 1.5271 0.05532 0.04883 -0.0999 0.0053 0.8234
13.750 1.5268 0.05799 0.05162 -0.0984 0.0049 0.8259
14.000 1.5270 0.06071 0.05447 -0.0972 0.0048 0.8285
14.250 1.5286 0.06335 0.05725 -0.0962 0.0046 0.8313
14.500 1.5289 0.06622 0.06024 -0.0953 0.0045 0.8341
14.750 1.5284 0.06923 0.06338 -0.0945 0.0044 0.8368
15.000 1.5269 0.07237 0.06666 -0.0938 0.0042 0.8395
15.250 1.5246 0.07570 0.07013 -0.0932 0.0041 0.8424
15.500 1.5218 0.07918 0.07374 -0.0927 0.0040 0.8457
15.750 1.5180 0.08289 0.07758 -0.0925 0.0039 0.8492
16.000 1.5129 0.08683 0.08166 -0.0924 0.0038 0.8526
16.250 1.5072 0.09087 0.08584 -0.0925 0.0038 0.8565
16.500 1.5002 0.09523 0.09034 -0.0927 0.0037 0.8608
16.750 1.4938 0.09959 0.09484 -0.0933 0.0037 0.8655
17.000 1.4860 0.10421 0.09961 -0.0940 0.0036 0.8707
17.250 1.4771 0.10908 0.10463 -0.0949 0.0036 0.8768
17.500 1.4692 0.11380 0.10950 -0.0960 0.0036 0.8846
18.000 1.4478 0.12319 0.11924 -0.0975 0.0035 0.9363
18.250 1.4382 0.12800 0.12419 -0.0990 0.0035 0.9999
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Polar data table (+)
Polar graphs
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