FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il) Reynolds number: 1,000,000 Max Cl/Cd: 161.95 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx62k153-il-1000000.txt Download as CSV file: xf-fx62k153-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0720 0.08334 0.08092 -0.1133 0.8292 0.0104
-11.250 -0.0746 0.07865 0.07624 -0.1148 0.8275 0.0105
-11.000 -0.2292 0.07143 0.06902 -0.1187 0.8358 0.0061
-10.750 -0.4698 0.02429 0.02015 -0.1428 0.8261 0.0046
-10.500 -0.4570 0.02186 0.01744 -0.1439 0.8235 0.0046
-10.250 -0.4384 0.02020 0.01555 -0.1448 0.8211 0.0046
-10.000 -0.4174 0.01891 0.01407 -0.1454 0.8188 0.0047
-9.750 -0.3946 0.01787 0.01287 -0.1459 0.8163 0.0048
-9.500 -0.3714 0.01692 0.01181 -0.1464 0.8146 0.0049
-9.250 -0.3471 0.01611 0.01089 -0.1468 0.8127 0.0050
-9.000 -0.3221 0.01536 0.01004 -0.1473 0.8109 0.0052
-8.750 -0.2965 0.01467 0.00926 -0.1478 0.8090 0.0055
-8.500 -0.2703 0.01407 0.00857 -0.1483 0.8071 0.0058
-8.250 -0.2431 0.01362 0.00804 -0.1489 0.8053 0.0061
-8.000 -0.2162 0.01297 0.00733 -0.1496 0.8034 0.0071
-7.750 -0.1876 0.01276 0.00709 -0.1503 0.8015 0.0082
-7.500 -0.1600 0.01231 0.00662 -0.1510 0.8001 0.0098
-7.250 -0.1316 0.01215 0.00647 -0.1515 0.7985 0.0111
-7.000 -0.1030 0.01205 0.00635 -0.1521 0.7968 0.0119
-6.750 -0.0746 0.01143 0.00569 -0.1531 0.7951 0.0135
-6.500 -0.0456 0.01119 0.00544 -0.1538 0.7935 0.0146
-6.250 -0.0164 0.01096 0.00517 -0.1546 0.7918 0.0155
-6.000 0.0131 0.01068 0.00484 -0.1554 0.7902 0.0165
-5.750 0.0434 0.01033 0.00446 -0.1566 0.7885 0.0185
-5.500 0.0735 0.01018 0.00430 -0.1575 0.7866 0.0202
-5.250 0.1029 0.01000 0.00411 -0.1582 0.7852 0.0215
-5.000 0.1337 0.00960 0.00369 -0.1594 0.7837 0.0248
-4.750 0.1640 0.00939 0.00347 -0.1603 0.7820 0.0282
-4.500 0.1954 0.00906 0.00320 -0.1615 0.7802 0.0433
-4.250 0.2270 0.00875 0.00300 -0.1629 0.7785 0.0733
-4.000 0.2598 0.00836 0.00279 -0.1647 0.7768 0.1316
-3.750 0.2984 0.00750 0.00247 -0.1684 0.7752 0.3002
-3.500 0.3412 0.00660 0.00220 -0.1731 0.7736 0.5093
-3.250 0.3745 0.00649 0.00222 -0.1747 0.7717 0.5716
-3.000 0.4051 0.00646 0.00225 -0.1754 0.7702 0.6021
-2.750 0.4351 0.00648 0.00227 -0.1760 0.7684 0.6172
-2.500 0.4651 0.00651 0.00228 -0.1766 0.7665 0.6277
-2.250 0.4947 0.00657 0.00234 -0.1771 0.7645 0.6394
-2.000 0.5238 0.00669 0.00247 -0.1773 0.7624 0.6535
-1.750 0.5539 0.00677 0.00248 -0.1779 0.7602 0.6592
-1.500 0.5836 0.00682 0.00251 -0.1785 0.7575 0.6622
-1.250 0.6123 0.00682 0.00253 -0.1788 0.7553 0.6649
-1.000 0.6413 0.00683 0.00254 -0.1792 0.7526 0.6679
-0.750 0.6707 0.00685 0.00253 -0.1797 0.7498 0.6709
-0.500 0.7005 0.00686 0.00252 -0.1803 0.7472 0.6735
-0.250 0.7300 0.00687 0.00251 -0.1808 0.7448 0.6759
0.000 0.7595 0.00693 0.00256 -0.1813 0.7424 0.6779
0.250 0.7881 0.00694 0.00260 -0.1817 0.7400 0.6801
0.500 0.8171 0.00696 0.00264 -0.1821 0.7375 0.6824
0.750 0.8462 0.00698 0.00267 -0.1825 0.7348 0.6848
1.000 0.8755 0.00700 0.00268 -0.1830 0.7320 0.6871
1.250 0.9051 0.00706 0.00270 -0.1836 0.7288 0.6891
1.500 0.9334 0.00703 0.00273 -0.1839 0.7251 0.6911
1.750 0.9615 0.00701 0.00274 -0.1841 0.7203 0.6929
2.000 0.9896 0.00703 0.00275 -0.1843 0.7152 0.6947
2.250 1.0176 0.00705 0.00281 -0.1845 0.7101 0.6967
2.500 1.0456 0.00706 0.00284 -0.1847 0.7045 0.6986
2.750 1.0736 0.00712 0.00288 -0.1849 0.6989 0.7006
3.000 1.1017 0.00714 0.00295 -0.1852 0.6926 0.7025
3.250 1.1289 0.00720 0.00298 -0.1852 0.6842 0.7042
3.500 1.1560 0.00723 0.00303 -0.1853 0.6740 0.7061
3.750 1.1822 0.00730 0.00311 -0.1851 0.6614 0.7078
4.000 1.2061 0.00746 0.00321 -0.1845 0.6417 0.7094
4.250 1.2304 0.00764 0.00336 -0.1839 0.6225 0.7113
4.500 1.2544 0.00785 0.00353 -0.1833 0.6045 0.7132
5.000 1.2991 0.00842 0.00397 -0.1816 0.5607 0.7169
5.250 1.3162 0.00894 0.00431 -0.1797 0.5249 0.7187
5.500 1.3298 0.00959 0.00474 -0.1772 0.4784 0.7204
5.750 1.3406 0.01033 0.00525 -0.1741 0.4283 0.7222
6.000 1.3482 0.01113 0.00582 -0.1705 0.3808 0.7239
6.250 1.3504 0.01204 0.00647 -0.1659 0.3267 0.7256
6.500 1.3548 0.01304 0.00722 -0.1619 0.2797 0.7275
6.750 1.3621 0.01395 0.00795 -0.1586 0.2435 0.7295
7.000 1.3697 0.01489 0.00872 -0.1554 0.2092 0.7314
7.250 1.3752 0.01598 0.00961 -0.1521 0.1714 0.7331
7.500 1.3813 0.01711 0.01058 -0.1490 0.1394 0.7346
7.750 1.3899 0.01816 0.01151 -0.1464 0.1152 0.7364
8.000 1.4004 0.01914 0.01242 -0.1442 0.0966 0.7380
8.250 1.4107 0.02016 0.01337 -0.1421 0.0806 0.7398
8.500 1.4228 0.02111 0.01428 -0.1402 0.0688 0.7417
8.750 1.4353 0.02205 0.01520 -0.1385 0.0592 0.7435
9.000 1.4477 0.02303 0.01615 -0.1368 0.0506 0.7453
9.250 1.4591 0.02409 0.01719 -0.1351 0.0420 0.7469
9.500 1.4701 0.02519 0.01826 -0.1333 0.0343 0.7484
9.750 1.4813 0.02629 0.01934 -0.1316 0.0278 0.7501
10.000 1.4915 0.02746 0.02051 -0.1299 0.0221 0.7520
10.250 1.5020 0.02863 0.02168 -0.1282 0.0178 0.7538
10.500 1.5109 0.02994 0.02299 -0.1263 0.0133 0.7555
10.750 1.5185 0.03134 0.02439 -0.1244 0.0080 0.7572
11.000 1.5237 0.03297 0.02601 -0.1222 0.0044 0.7589
11.250 1.5322 0.03438 0.02748 -0.1205 0.0037 0.7606
11.500 1.5409 0.03579 0.02895 -0.1188 0.0033 0.7623
11.750 1.5499 0.03720 0.03042 -0.1173 0.0031 0.7639
12.000 1.5586 0.03865 0.03197 -0.1157 0.0030 0.7660
12.250 1.5669 0.04017 0.03357 -0.1142 0.0029 0.7678
12.500 1.5739 0.04182 0.03531 -0.1127 0.0027 0.7695
12.750 1.5795 0.04364 0.03721 -0.1111 0.0026 0.7713
13.000 1.5856 0.04542 0.03907 -0.1096 0.0025 0.7731
13.250 1.5877 0.04763 0.04138 -0.1078 0.0023 0.7749
13.500 1.5891 0.04997 0.04383 -0.1061 0.0022 0.7765
13.750 1.5875 0.05267 0.04665 -0.1043 0.0022 0.7781
14.000 1.5919 0.05482 0.04890 -0.1031 0.0021 0.7802
14.250 1.5949 0.05714 0.05132 -0.1019 0.0021 0.7823
14.500 1.5962 0.05971 0.05400 -0.1007 0.0021 0.7843
14.750 1.5967 0.06243 0.05683 -0.0996 0.0020 0.7863
15.000 1.5960 0.06535 0.05985 -0.0986 0.0019 0.7882
15.250 1.5951 0.06834 0.06296 -0.0977 0.0019 0.7902
15.500 1.5925 0.07159 0.06631 -0.0969 0.0019 0.7920
15.750 1.5894 0.07499 0.06983 -0.0963 0.0019 0.7939
16.000 1.5846 0.07872 0.07368 -0.0958 0.0018 0.7960
16.250 1.5798 0.08250 0.07759 -0.0955 0.0018 0.7981
16.500 1.5732 0.08662 0.08184 -0.0954 0.0018 0.8002
16.750 1.5674 0.09067 0.08602 -0.0955 0.0018 0.8026
17.000 1.5600 0.09506 0.09054 -0.0957 0.0018 0.8050
17.250 1.5512 0.09973 0.09533 -0.0962 0.0018 0.8071
17.500 1.5433 0.10440 0.10014 -0.0970 0.0018 0.8097
17.750 1.5344 0.10931 0.10519 -0.0980 0.0018 0.8122
18.000 1.5242 0.11448 0.11050 -0.0993 0.0018 0.8149
18.250 1.5146 0.11965 0.11579 -0.1008 0.0017 0.8177
|
Polar data table (+)
Polar graphs
<< Back to FX 62-K-153/20 AIRFOIL (fx62k153-il)