EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il) Reynolds number: 500,000 Max Cl/Cd: 98.7 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stf86361-il-500000-n5.txt Download as CSV file: xf-stf86361-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1767 0.08659 0.08358 -0.1323 0.8901 0.0056
-11.750 -0.1787 0.08115 0.07816 -0.1355 0.8890 0.0057
-11.500 -0.1824 0.07503 0.07205 -0.1396 0.8878 0.0056
-11.250 -0.1914 0.06617 0.06319 -0.1470 0.8864 0.0055
-11.000 -0.2068 0.05890 0.05582 -0.1530 0.8848 0.0054
-10.750 -0.2222 0.05342 0.05023 -0.1566 0.8831 0.0054
-10.500 -0.2355 0.04884 0.04550 -0.1590 0.8812 0.0054
-10.250 -0.2459 0.04472 0.04123 -0.1607 0.8794 0.0054
-10.000 -0.2528 0.04089 0.03719 -0.1618 0.8777 0.0056
-9.750 -0.2527 0.03693 0.03293 -0.1621 0.8762 0.0057
-9.500 -0.2480 0.03291 0.02858 -0.1618 0.8748 0.0059
-9.250 -0.2379 0.02892 0.02412 -0.1610 0.8736 0.0065
-9.000 -0.2247 0.02625 0.02114 -0.1609 0.8726 0.0068
-8.750 -0.2057 0.02465 0.01935 -0.1609 0.8718 0.0069
-8.500 -0.1847 0.02330 0.01780 -0.1610 0.8711 0.0071
-8.250 -0.1623 0.02208 0.01642 -0.1611 0.8704 0.0074
-8.000 -0.1390 0.02085 0.01500 -0.1611 0.8698 0.0079
-7.750 -0.1148 0.01962 0.01357 -0.1609 0.8691 0.0085
-7.500 -0.0899 0.01847 0.01219 -0.1607 0.8684 0.0092
-7.250 -0.0638 0.01790 0.01141 -0.1607 0.8678 0.0100
-7.000 -0.0407 0.01699 0.01051 -0.1605 0.8673 0.0108
-6.750 -0.0177 0.01652 0.01003 -0.1602 0.8666 0.0114
-6.500 0.0050 0.01597 0.00945 -0.1597 0.8659 0.0121
-6.250 0.0275 0.01549 0.00893 -0.1591 0.8651 0.0128
-6.000 0.0501 0.01509 0.00847 -0.1586 0.8643 0.0136
-5.750 0.0739 0.01487 0.00820 -0.1583 0.8634 0.0144
-5.500 0.0958 0.01440 0.00771 -0.1578 0.8623 0.0153
-5.250 0.1179 0.01385 0.00719 -0.1575 0.8612 0.0160
-5.000 0.1419 0.01347 0.00680 -0.1575 0.8604 0.0166
-4.750 0.1670 0.01315 0.00646 -0.1577 0.8596 0.0173
-4.500 0.1930 0.01287 0.00616 -0.1580 0.8588 0.0179
-4.250 0.2200 0.01264 0.00590 -0.1585 0.8580 0.0189
-4.000 0.2478 0.01244 0.00569 -0.1591 0.8572 0.0197
-3.750 0.2759 0.01226 0.00547 -0.1597 0.8566 0.0200
-3.500 0.3043 0.01210 0.00527 -0.1604 0.8560 0.0204
-3.250 0.3335 0.01193 0.00505 -0.1612 0.8554 0.0216
-3.000 0.3632 0.01181 0.00490 -0.1621 0.8548 0.0230
-2.750 0.3929 0.01174 0.00479 -0.1630 0.8543 0.0244
-2.500 0.4225 0.01170 0.00474 -0.1639 0.8538 0.0266
-2.250 0.4572 0.00978 0.00452 -0.1684 0.8528 0.5771
-2.000 0.4764 0.01010 0.00490 -0.1669 0.8505 0.6135
-1.750 0.4994 0.01034 0.00514 -0.1661 0.8483 0.6278
-1.500 0.5255 0.01047 0.00528 -0.1660 0.8464 0.6359
-1.250 0.5542 0.01054 0.00533 -0.1664 0.8448 0.6433
-1.000 0.5830 0.01064 0.00546 -0.1667 0.8434 0.6506
-0.750 0.6126 0.01080 0.00565 -0.1671 0.8422 0.6618
-0.500 0.6447 0.01074 0.00559 -0.1682 0.8410 0.6637
-0.250 0.6775 0.01067 0.00552 -0.1696 0.8400 0.6645
0.000 0.6945 0.01084 0.00573 -0.1678 0.8368 0.6652
0.250 0.7153 0.01093 0.00585 -0.1667 0.8337 0.6658
0.500 0.7418 0.01093 0.00588 -0.1667 0.8317 0.6665
0.750 0.7701 0.01092 0.00590 -0.1672 0.8302 0.6671
1.000 0.7993 0.01090 0.00591 -0.1679 0.8289 0.6679
1.250 0.8313 0.01080 0.00584 -0.1691 0.8276 0.6687
1.500 0.8595 0.01064 0.00572 -0.1694 0.8239 0.6694
1.750 0.8752 0.01051 0.00563 -0.1670 0.8162 0.6701
2.000 0.9020 0.01021 0.00536 -0.1668 0.8098 0.6707
2.250 0.9103 0.01030 0.00550 -0.1630 0.8026 0.6713
2.500 0.9256 0.01035 0.00560 -0.1606 0.7944 0.6720
2.750 0.9348 0.01061 0.00592 -0.1571 0.7786 0.6726
3.000 0.9663 0.00979 0.00471 -0.1572 0.7000 0.6731
3.250 0.9485 0.01118 0.00545 -0.1481 0.5945 0.6738
3.750 0.9177 0.01451 0.00778 -0.1328 0.4079 0.6752
4.000 0.9104 0.01620 0.00885 -0.1272 0.2869 0.6757
4.250 0.9122 0.01759 0.00973 -0.1232 0.1864 0.6762
4.500 0.9194 0.01874 0.01049 -0.1203 0.1061 0.6767
4.750 0.9291 0.01980 0.01125 -0.1177 0.0427 0.6772
5.000 0.9447 0.02052 0.01186 -0.1161 0.0195 0.6777
5.250 0.9636 0.02103 0.01239 -0.1150 0.0165 0.6782
5.500 0.9826 0.02154 0.01296 -0.1140 0.0148 0.6788
5.750 1.0018 0.02203 0.01351 -0.1130 0.0143 0.6794
6.000 1.0203 0.02257 0.01411 -0.1119 0.0136 0.6799
6.250 1.0383 0.02314 0.01476 -0.1107 0.0129 0.6805
6.500 1.0557 0.02377 0.01545 -0.1095 0.0124 0.6811
6.750 1.0725 0.02444 0.01619 -0.1081 0.0119 0.6818
7.000 1.0885 0.02516 0.01697 -0.1067 0.0115 0.6824
7.250 1.1035 0.02595 0.01784 -0.1051 0.0111 0.6830
7.500 1.1171 0.02685 0.01880 -0.1034 0.0106 0.6836
7.750 1.1279 0.02797 0.02001 -0.1012 0.0100 0.6844
8.000 1.1365 0.02928 0.02142 -0.0987 0.0095 0.6851
8.250 1.1520 0.03006 0.02226 -0.0973 0.0092 0.6859
8.500 1.1657 0.03099 0.02328 -0.0957 0.0089 0.6866
8.750 1.1790 0.03199 0.02436 -0.0941 0.0086 0.6872
9.000 1.1920 0.03303 0.02550 -0.0924 0.0083 0.6877
9.250 1.2054 0.03402 0.02658 -0.0908 0.0078 0.6883
9.500 1.2188 0.03500 0.02766 -0.0894 0.0074 0.6889
9.750 1.2327 0.03592 0.02865 -0.0881 0.0069 0.6895
10.000 1.2457 0.03694 0.02973 -0.0867 0.0066 0.6902
10.250 1.2569 0.03815 0.03102 -0.0850 0.0063 0.6908
10.500 1.2649 0.03980 0.03279 -0.0829 0.0060 0.6915
10.750 1.2755 0.04122 0.03434 -0.0811 0.0058 0.6921
11.000 1.2871 0.04249 0.03576 -0.0796 0.0056 0.6928
11.250 1.2975 0.04395 0.03738 -0.0779 0.0053 0.6936
11.500 1.3069 0.04552 0.03912 -0.0762 0.0050 0.6943
11.750 1.3146 0.04730 0.04109 -0.0743 0.0048 0.6950
12.000 1.3213 0.04911 0.04308 -0.0724 0.0046 0.6958
12.250 1.3262 0.05106 0.04519 -0.0706 0.0044 0.6966
12.500 1.3308 0.05288 0.04716 -0.0689 0.0042 0.6974
12.750 1.3348 0.05475 0.04916 -0.0674 0.0040 0.6982
13.000 1.3379 0.05675 0.05128 -0.0659 0.0039 0.6990
13.250 1.3415 0.05864 0.05326 -0.0647 0.0038 0.6998
13.500 1.3428 0.06092 0.05567 -0.0633 0.0037 0.7006
13.750 1.3429 0.06340 0.05825 -0.0622 0.0036 0.7014
14.000 1.3355 0.06694 0.06198 -0.0606 0.0035 0.7020
14.250 1.3280 0.07068 0.06594 -0.0594 0.0034 0.7026
14.500 1.3208 0.07448 0.06997 -0.0584 0.0034 0.7033
14.750 1.3093 0.07903 0.07477 -0.0577 0.0033 0.7040
15.000 1.2930 0.08449 0.08049 -0.0574 0.0032 0.7045
15.250 1.2749 0.09052 0.08678 -0.0579 0.0032 0.7051
15.500 1.2556 0.09711 0.09360 -0.0592 0.0031 0.7056
15.750 1.2341 0.10447 0.10119 -0.0613 0.0031 0.7062
16.000 1.2120 0.11249 0.10943 -0.0646 0.0031 0.7067
16.250 1.1911 0.12097 0.11810 -0.0688 0.0031 0.7072
16.500 1.1652 0.13139 0.12873 -0.0747 0.0031 0.7076
16.750 1.1431 0.14190 0.13941 -0.0812 0.0032 0.7079
17.000 1.1209 0.15347 0.15111 -0.0885 0.0033 0.7082
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Polar data table (+)
Polar graphs
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