EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.14 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stf86361-il-1000000.txt Download as CSV file: xf-stf86361-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1653 0.08701 0.08474 -0.1330 0.8935 0.0086
-11.750 -0.1636 0.08188 0.07960 -0.1362 0.8924 0.0087
-11.500 -0.1628 0.07581 0.07354 -0.1403 0.8911 0.0087
-11.250 -0.1661 0.06710 0.06480 -0.1476 0.8904 0.0087
-11.000 -0.1760 0.06087 0.05850 -0.1529 0.8894 0.0087
-10.750 -0.1868 0.05597 0.05351 -0.1566 0.8882 0.0087
-10.500 -0.1970 0.05181 0.04925 -0.1592 0.8869 0.0087
-10.250 -0.2057 0.04811 0.04543 -0.1612 0.8854 0.0087
-10.000 -0.2128 0.04483 0.04202 -0.1628 0.8837 0.0087
-9.750 -0.2134 0.04158 0.03857 -0.1645 0.8821 0.0087
-9.500 -0.2093 0.03845 0.03522 -0.1653 0.8809 0.0087
-9.250 -0.2010 0.03547 0.03201 -0.1658 0.8799 0.0087
-9.000 -0.1973 0.03045 0.02673 -0.1663 0.8787 0.0089
-8.750 -0.1808 0.02818 0.02431 -0.1668 0.8779 0.0090
-8.500 -0.1623 0.02614 0.02209 -0.1671 0.8770 0.0091
-8.250 -0.1435 0.02340 0.01908 -0.1669 0.8759 0.0081
-8.000 -0.1243 0.01991 0.01518 -0.1662 0.8754 0.0077
-7.750 -0.1008 0.01813 0.01309 -0.1659 0.8750 0.0092
-7.500 -0.0755 0.01785 0.01282 -0.1665 0.8747 0.0099
-7.250 -0.0503 0.01689 0.01170 -0.1664 0.8742 0.0106
-7.000 -0.0251 0.01586 0.01053 -0.1661 0.8737 0.0109
-6.750 0.0002 0.01510 0.00965 -0.1659 0.8730 0.0112
-6.500 0.0245 0.01440 0.00896 -0.1658 0.8724 0.0121
-6.250 0.0498 0.01401 0.00854 -0.1659 0.8718 0.0132
-6.000 0.0751 0.01354 0.00797 -0.1656 0.8712 0.0140
-5.750 0.0978 0.01283 0.00731 -0.1651 0.8705 0.0151
-5.500 0.1225 0.01248 0.00696 -0.1651 0.8699 0.0160
-5.250 0.1477 0.01217 0.00662 -0.1651 0.8691 0.0167
-5.000 0.1726 0.01172 0.00617 -0.1652 0.8682 0.0177
-4.750 0.1984 0.01136 0.00583 -0.1656 0.8674 0.0190
-4.500 0.2251 0.01111 0.00556 -0.1659 0.8668 0.0198
-4.250 0.2522 0.01094 0.00537 -0.1663 0.8661 0.0203
-4.000 0.2797 0.01057 0.00500 -0.1670 0.8654 0.0211
-3.750 0.3081 0.01037 0.00479 -0.1677 0.8647 0.0222
-3.500 0.3370 0.01022 0.00463 -0.1685 0.8639 0.0233
-3.250 0.3664 0.01005 0.00444 -0.1693 0.8632 0.0245
-3.000 0.3970 0.00992 0.00430 -0.1703 0.8621 0.0262
-2.750 0.4271 0.00990 0.00425 -0.1712 0.8606 0.0296
-2.500 0.4604 0.00798 0.00402 -0.1752 0.8592 0.6151
-2.250 0.4871 0.00823 0.00429 -0.1751 0.8581 0.6346
-2.000 0.5130 0.00846 0.00457 -0.1748 0.8571 0.6442
-1.750 0.5393 0.00871 0.00484 -0.1746 0.8558 0.6517
-1.500 0.5661 0.00883 0.00497 -0.1746 0.8543 0.6572
-1.250 0.5929 0.00891 0.00508 -0.1746 0.8526 0.6612
-1.000 0.6204 0.00902 0.00522 -0.1746 0.8511 0.6653
-0.750 0.6489 0.00911 0.00532 -0.1750 0.8497 0.6693
-0.500 0.6787 0.00908 0.00528 -0.1757 0.8486 0.6702
-0.250 0.7088 0.00905 0.00525 -0.1766 0.8476 0.6709
0.000 0.7392 0.00903 0.00524 -0.1776 0.8466 0.6713
0.250 0.7707 0.00899 0.00520 -0.1787 0.8454 0.6718
0.500 0.8003 0.00908 0.00529 -0.1795 0.8433 0.6724
0.750 0.8257 0.00903 0.00527 -0.1793 0.8416 0.6729
1.000 0.8509 0.00901 0.00528 -0.1791 0.8393 0.6732
1.250 0.8777 0.00891 0.00523 -0.1792 0.8365 0.6735
1.500 0.9119 0.00845 0.00476 -0.1807 0.8321 0.6742
1.750 0.9484 0.00810 0.00437 -0.1827 0.8272 0.6749
2.000 0.9687 0.00784 0.00417 -0.1813 0.8208 0.6756
2.250 0.9994 0.00741 0.00373 -0.1820 0.8116 0.6763
2.500 1.0142 0.00715 0.00349 -0.1791 0.7950 0.6771
2.750 1.0232 0.00705 0.00335 -0.1751 0.7612 0.6779
3.000 1.0102 0.00766 0.00355 -0.1664 0.6840 0.6785
3.250 0.9950 0.00889 0.00438 -0.1578 0.6059 0.6791
3.500 0.9843 0.01012 0.00526 -0.1506 0.5359 0.6797
3.750 0.9738 0.01156 0.00625 -0.1437 0.4440 0.6802
4.000 0.9721 0.01279 0.00709 -0.1387 0.3606 0.6808
4.250 0.9654 0.01439 0.00810 -0.1330 0.2448 0.6813
4.500 0.9622 0.01596 0.00907 -0.1281 0.1287 0.6818
4.750 0.9636 0.01740 0.01000 -0.1239 0.0306 0.6823
5.000 0.9802 0.01801 0.01055 -0.1224 0.0182 0.6828
5.250 0.9992 0.01848 0.01104 -0.1213 0.0162 0.6833
5.500 1.0175 0.01900 0.01159 -0.1200 0.0149 0.6838
5.750 1.0358 0.01952 0.01214 -0.1188 0.0142 0.6844
6.000 1.0542 0.02004 0.01270 -0.1177 0.0136 0.6849
6.250 1.0716 0.02062 0.01331 -0.1163 0.0129 0.6855
6.500 1.0861 0.02141 0.01413 -0.1145 0.0122 0.6862
6.750 1.1031 0.02201 0.01478 -0.1132 0.0115 0.6869
7.000 1.1198 0.02264 0.01546 -0.1118 0.0109 0.6876
7.250 1.1352 0.02334 0.01621 -0.1102 0.0104 0.6881
7.500 1.1477 0.02425 0.01714 -0.1082 0.0099 0.6886
7.750 1.1556 0.02550 0.01845 -0.1055 0.0095 0.6891
8.000 1.1722 0.02616 0.01918 -0.1042 0.0092 0.6896
8.250 1.1877 0.02690 0.01998 -0.1027 0.0088 0.6901
8.500 1.2033 0.02763 0.02076 -0.1014 0.0082 0.6905
8.750 1.2181 0.02839 0.02155 -0.1000 0.0077 0.6910
9.000 1.2264 0.02971 0.02293 -0.0975 0.0071 0.6913
9.250 1.2426 0.03042 0.02372 -0.0963 0.0068 0.6917
9.500 1.2565 0.03134 0.02472 -0.0947 0.0064 0.6921
9.750 1.2700 0.03228 0.02573 -0.0931 0.0060 0.6925
10.000 1.2836 0.03320 0.02672 -0.0917 0.0058 0.6935
10.250 1.2961 0.03421 0.02779 -0.0901 0.0056 0.6944
10.500 1.3067 0.03543 0.02908 -0.0883 0.0053 0.6952
10.750 1.3144 0.03738 0.03118 -0.0858 0.0051 0.6959
11.000 1.3266 0.03841 0.03234 -0.0842 0.0050 0.6968
11.250 1.3376 0.03965 0.03371 -0.0825 0.0048 0.6975
11.500 1.3471 0.04102 0.03522 -0.0807 0.0046 0.6983
11.750 1.3557 0.04249 0.03684 -0.0788 0.0044 0.6991
12.000 1.3634 0.04402 0.03851 -0.0770 0.0042 0.6998
12.250 1.3702 0.04550 0.04010 -0.0752 0.0040 0.7006
12.500 1.3766 0.04698 0.04168 -0.0735 0.0039 0.7014
12.750 1.3828 0.04849 0.04328 -0.0720 0.0037 0.7022
13.000 1.3890 0.04998 0.04485 -0.0706 0.0036 0.7031
13.250 1.3927 0.05185 0.04681 -0.0690 0.0035 0.7039
13.500 1.3696 0.05703 0.05238 -0.0647 0.0032 0.7043
13.750 1.3718 0.05917 0.05466 -0.0633 0.0031 0.7051
14.000 1.3646 0.06255 0.05825 -0.0614 0.0031 0.7058
14.250 1.3549 0.06638 0.06230 -0.0595 0.0029 0.7066
14.500 1.3375 0.07132 0.06750 -0.0577 0.0029 0.7072
14.750 1.3127 0.07752 0.07398 -0.0564 0.0028 0.7076
15.000 1.2853 0.08451 0.08124 -0.0560 0.0028 0.7080
15.250 1.2524 0.09291 0.08993 -0.0568 0.0028 0.7083
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