EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il) Reynolds number: 1,000,000 Max Cl/Cd: 142.68 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stf86361-il-1000000-n5.txt Download as CSV file: xf-stf86361-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STF 863-615 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2032 0.08625 0.08380 -0.1285 0.8656 0.0033
-12.000 -0.2094 0.07970 0.07727 -0.1323 0.8649 0.0033
-11.750 -0.2207 0.07107 0.06868 -0.1383 0.8640 0.0034
-11.500 -0.2434 0.05954 0.05709 -0.1485 0.8628 0.0033
-11.250 -0.2657 0.05268 0.05012 -0.1533 0.8614 0.0033
-11.000 -0.2860 0.04709 0.04438 -0.1562 0.8599 0.0033
-10.750 -0.3052 0.04162 0.03872 -0.1582 0.8581 0.0034
-10.500 -0.3223 0.03539 0.03214 -0.1597 0.8565 0.0036
-10.250 -0.3308 0.02838 0.02460 -0.1597 0.8551 0.0038
-10.000 -0.3254 0.02321 0.01891 -0.1593 0.8541 0.0040
-9.750 -0.3114 0.01965 0.01491 -0.1589 0.8534 0.0043
-9.500 -0.2869 0.01906 0.01424 -0.1594 0.8530 0.0045
-9.250 -0.2618 0.01857 0.01368 -0.1599 0.8526 0.0047
-9.000 -0.2368 0.01795 0.01297 -0.1604 0.8522 0.0049
-8.750 -0.2123 0.01700 0.01191 -0.1605 0.8517 0.0054
-8.500 -0.1896 0.01546 0.01019 -0.1600 0.8513 0.0061
-8.250 -0.1663 0.01443 0.00906 -0.1598 0.8508 0.0065
-8.000 -0.1415 0.01382 0.00838 -0.1600 0.8503 0.0069
-7.750 -0.1143 0.01362 0.00816 -0.1606 0.8498 0.0072
-7.500 -0.0874 0.01339 0.00790 -0.1611 0.8494 0.0075
-7.250 -0.0610 0.01305 0.00751 -0.1615 0.8489 0.0080
-7.000 -0.0349 0.01265 0.00708 -0.1618 0.8483 0.0087
-6.750 -0.0082 0.01234 0.00672 -0.1622 0.8477 0.0096
-6.500 0.0187 0.01207 0.00641 -0.1626 0.8471 0.0100
-6.250 0.0440 0.01148 0.00580 -0.1629 0.8465 0.0104
-6.000 0.0706 0.01111 0.00541 -0.1634 0.8460 0.0109
-5.750 0.0979 0.01082 0.00512 -0.1640 0.8456 0.0114
-5.500 0.1256 0.01058 0.00488 -0.1646 0.8451 0.0122
-5.250 0.1533 0.01034 0.00462 -0.1652 0.8446 0.0131
-5.000 0.1812 0.01007 0.00432 -0.1658 0.8442 0.0137
-4.750 0.2094 0.00985 0.00409 -0.1665 0.8437 0.0141
-4.500 0.2377 0.00965 0.00387 -0.1672 0.8433 0.0144
-4.250 0.2662 0.00947 0.00368 -0.1679 0.8428 0.0147
-4.000 0.2947 0.00919 0.00338 -0.1686 0.8422 0.0153
-3.750 0.3236 0.00897 0.00314 -0.1694 0.8415 0.0160
-3.500 0.3527 0.00882 0.00297 -0.1702 0.8407 0.0166
-3.250 0.3821 0.00872 0.00285 -0.1710 0.8398 0.0175
-3.000 0.4099 0.00861 0.00274 -0.1715 0.8390 0.0185
-2.750 0.4373 0.00853 0.00266 -0.1718 0.8379 0.0193
-2.500 0.4649 0.00845 0.00260 -0.1722 0.8369 0.0199
-2.250 0.4927 0.00839 0.00254 -0.1726 0.8358 0.0205
-2.000 0.5207 0.00833 0.00249 -0.1731 0.8347 0.0229
-1.750 0.5488 0.00826 0.00245 -0.1735 0.8335 0.0263
-1.500 0.5840 0.00645 0.00216 -0.1777 0.8324 0.6039
-1.250 0.6126 0.00653 0.00227 -0.1781 0.8313 0.6212
-1.000 0.6416 0.00660 0.00233 -0.1787 0.8300 0.6301
-0.750 0.6704 0.00665 0.00240 -0.1791 0.8286 0.6359
-0.500 0.6996 0.00674 0.00250 -0.1797 0.8271 0.6429
-0.250 0.7285 0.00679 0.00254 -0.1802 0.8253 0.6461
0.000 0.7546 0.00678 0.00257 -0.1802 0.8235 0.6466
0.250 0.7812 0.00678 0.00261 -0.1803 0.8215 0.6473
0.500 0.8084 0.00678 0.00264 -0.1805 0.8195 0.6478
0.750 0.8355 0.00668 0.00255 -0.1806 0.8147 0.6482
1.000 0.8605 0.00662 0.00251 -0.1802 0.8087 0.6487
1.250 0.8850 0.00660 0.00253 -0.1798 0.8032 0.6491
1.500 0.9097 0.00656 0.00251 -0.1794 0.7954 0.6496
1.750 0.9274 0.00650 0.00242 -0.1773 0.7696 0.6501
2.000 0.9156 0.00699 0.00251 -0.1687 0.6928 0.6507
2.250 0.9003 0.00820 0.00329 -0.1601 0.6096 0.6513
2.500 0.8922 0.00935 0.00409 -0.1532 0.5383 0.6519
2.750 0.8810 0.01081 0.00505 -0.1461 0.4373 0.6526
3.000 0.8772 0.01216 0.00589 -0.1407 0.3319 0.6533
3.250 0.8784 0.01340 0.00668 -0.1363 0.2381 0.6539
3.500 0.8826 0.01459 0.00742 -0.1325 0.1415 0.6544
3.750 0.8922 0.01555 0.00805 -0.1298 0.0690 0.6549
4.000 0.9054 0.01636 0.00862 -0.1276 0.0197 0.6554
4.250 0.9262 0.01673 0.00898 -0.1268 0.0145 0.6558
4.500 0.9473 0.01708 0.00935 -0.1260 0.0134 0.6563
4.750 0.9679 0.01746 0.00976 -0.1252 0.0125 0.6568
5.000 0.9880 0.01787 0.01019 -0.1243 0.0115 0.6572
5.250 1.0077 0.01832 0.01066 -0.1233 0.0104 0.6576
5.500 1.0266 0.01881 0.01121 -0.1222 0.0098 0.6580
5.750 1.0453 0.01932 0.01176 -0.1210 0.0095 0.6584
6.000 1.0644 0.01979 0.01228 -0.1200 0.0094 0.6588
6.250 1.0832 0.02029 0.01281 -0.1189 0.0092 0.6592
6.500 1.1018 0.02080 0.01336 -0.1178 0.0090 0.6596
6.750 1.1200 0.02133 0.01395 -0.1167 0.0088 0.6602
7.000 1.1379 0.02188 0.01455 -0.1155 0.0084 0.6607
7.250 1.1557 0.02244 0.01516 -0.1143 0.0080 0.6613
7.500 1.1728 0.02305 0.01581 -0.1131 0.0076 0.6619
7.750 1.1895 0.02368 0.01650 -0.1118 0.0073 0.6625
8.000 1.2061 0.02432 0.01719 -0.1105 0.0070 0.6632
8.250 1.2222 0.02499 0.01790 -0.1092 0.0067 0.6638
8.500 1.2366 0.02578 0.01874 -0.1076 0.0063 0.6644
8.750 1.2457 0.02698 0.02002 -0.1051 0.0059 0.6650
9.000 1.2622 0.02763 0.02073 -0.1040 0.0058 0.6655
9.250 1.2782 0.02831 0.02147 -0.1027 0.0056 0.6661
9.500 1.2930 0.02909 0.02231 -0.1013 0.0054 0.6667
9.750 1.3075 0.02989 0.02318 -0.0999 0.0052 0.6673
10.000 1.3218 0.03073 0.02409 -0.0985 0.0050 0.6679
10.250 1.3353 0.03161 0.02504 -0.0970 0.0047 0.6685
10.500 1.3495 0.03244 0.02593 -0.0957 0.0045 0.6691
10.750 1.3647 0.03319 0.02672 -0.0945 0.0042 0.6697
11.000 1.3803 0.03392 0.02749 -0.0935 0.0040 0.6704
11.250 1.3944 0.03477 0.02837 -0.0923 0.0038 0.6710
11.500 1.4070 0.03574 0.02939 -0.0909 0.0036 0.6716
11.750 1.4158 0.03705 0.03078 -0.0890 0.0034 0.6721
12.000 1.4279 0.03809 0.03190 -0.0877 0.0033 0.6727
12.250 1.4373 0.03935 0.03325 -0.0860 0.0032 0.6732
12.500 1.4470 0.04061 0.03460 -0.0844 0.0031 0.6738
12.750 1.4555 0.04199 0.03608 -0.0828 0.0029 0.6745
13.000 1.4640 0.04339 0.03757 -0.0812 0.0028 0.6753
13.250 1.4727 0.04480 0.03908 -0.0797 0.0027 0.6760
13.500 1.4794 0.04641 0.04078 -0.0781 0.0026 0.6768
13.750 1.4877 0.04787 0.04235 -0.0768 0.0025 0.6775
14.000 1.4949 0.04948 0.04403 -0.0754 0.0024 0.6783
14.250 1.5012 0.05119 0.04583 -0.0741 0.0023 0.6791
14.500 1.5065 0.05304 0.04777 -0.0728 0.0022 0.6799
14.750 1.5116 0.05495 0.04977 -0.0715 0.0021 0.6807
15.000 1.5134 0.05726 0.05219 -0.0701 0.0020 0.6815
15.250 1.5120 0.05997 0.05503 -0.0687 0.0019 0.6823
15.500 1.5063 0.06321 0.05842 -0.0672 0.0019 0.6830
15.750 1.5043 0.06614 0.06149 -0.0661 0.0018 0.6838
16.000 1.4986 0.06962 0.06512 -0.0651 0.0018 0.6845
16.250 1.4949 0.07296 0.06859 -0.0644 0.0018 0.6852
16.500 1.4896 0.07660 0.07238 -0.0639 0.0018 0.6860
16.750 1.4826 0.08058 0.07650 -0.0637 0.0018 0.6867
17.000 1.4717 0.08521 0.08129 -0.0638 0.0018 0.6873
17.500 1.4502 0.09500 0.09139 -0.0650 0.0017 0.6888
17.750 1.4381 0.10035 0.09691 -0.0663 0.0017 0.6896
18.000 1.4237 0.10630 0.10302 -0.0680 0.0017 0.6903
18.250 1.4046 0.11328 0.11018 -0.0706 0.0017 0.6909
18.500 1.3896 0.11981 0.11686 -0.0733 0.0017 0.6915
18.750 1.3686 0.12777 0.12499 -0.0771 0.0017 0.6920
19.000 1.3480 0.13605 0.13344 -0.0815 0.0017 0.6925
19.250 1.3263 0.14502 0.14255 -0.0867 0.0017 0.6929
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