EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.5 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ste87151-il-1000000-n5.txt Download as CSV file: xf-ste87151-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STE 871-514 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6301 0.03450 0.03121 -0.1185 0.8820 0.0044
-11.750 -0.6362 0.03134 0.02779 -0.1174 0.8810 0.0044
-11.500 -0.6319 0.02922 0.02548 -0.1165 0.8801 0.0045
-11.250 -0.6264 0.02708 0.02313 -0.1154 0.8793 0.0045
-11.000 -0.6171 0.02536 0.02120 -0.1144 0.8785 0.0046
-10.750 -0.6040 0.02361 0.01923 -0.1136 0.8779 0.0046
-10.500 -0.5883 0.02202 0.01743 -0.1129 0.8773 0.0047
-10.250 -0.5700 0.02071 0.01594 -0.1124 0.8767 0.0047
-10.000 -0.5498 0.01963 0.01470 -0.1120 0.8762 0.0048
-9.750 -0.5285 0.01864 0.01358 -0.1118 0.8757 0.0049
-9.500 -0.5064 0.01775 0.01256 -0.1115 0.8753 0.0050
-9.250 -0.4835 0.01695 0.01164 -0.1113 0.8748 0.0052
-9.000 -0.4601 0.01624 0.01082 -0.1112 0.8743 0.0053
-8.750 -0.4362 0.01558 0.01008 -0.1110 0.8739 0.0055
-8.500 -0.4119 0.01501 0.00942 -0.1110 0.8734 0.0056
-8.250 -0.3874 0.01448 0.00883 -0.1109 0.8729 0.0058
-8.000 -0.3624 0.01404 0.00832 -0.1109 0.8724 0.0059
-7.750 -0.3372 0.01362 0.00785 -0.1109 0.8721 0.0060
-7.500 -0.3118 0.01322 0.00742 -0.1109 0.8717 0.0061
-7.250 -0.2882 0.01260 0.00674 -0.1107 0.8713 0.0063
-7.000 -0.2630 0.01220 0.00632 -0.1107 0.8710 0.0066
-6.750 -0.2373 0.01188 0.00598 -0.1107 0.8706 0.0068
-6.500 -0.2114 0.01159 0.00568 -0.1108 0.8702 0.0071
-6.250 -0.1853 0.01131 0.00539 -0.1108 0.8698 0.0073
-6.000 -0.1592 0.01105 0.00511 -0.1109 0.8693 0.0077
-5.750 -0.1328 0.01081 0.00486 -0.1110 0.8687 0.0081
-5.500 -0.1062 0.01061 0.00465 -0.1111 0.8679 0.0085
-5.250 -0.0801 0.01033 0.00435 -0.1111 0.8671 0.0092
-5.000 -0.0534 0.01012 0.00414 -0.1112 0.8662 0.0099
-4.750 -0.0265 0.00993 0.00396 -0.1114 0.8655 0.0107
-4.500 0.0006 0.00977 0.00379 -0.1115 0.8650 0.0115
-4.250 0.0275 0.00960 0.00364 -0.1117 0.8645 0.0134
-4.000 0.0548 0.00946 0.00351 -0.1119 0.8639 0.0161
-3.750 0.0821 0.00931 0.00339 -0.1121 0.8633 0.0211
-3.500 0.1095 0.00916 0.00327 -0.1123 0.8626 0.0281
-3.250 0.1368 0.00897 0.00315 -0.1126 0.8619 0.0447
-3.000 0.1637 0.00869 0.00302 -0.1128 0.8611 0.0868
-2.750 0.1898 0.00823 0.00286 -0.1131 0.8601 0.1761
-2.500 0.2141 0.00742 0.00265 -0.1134 0.8591 0.3551
-2.250 0.2393 0.00651 0.00239 -0.1140 0.8581 0.5557
-2.000 0.2655 0.00614 0.00255 -0.1141 0.8573 0.7150
-1.750 0.2939 0.00629 0.00269 -0.1143 0.8567 0.7387
-1.500 0.3217 0.00644 0.00287 -0.1143 0.8560 0.7487
-1.250 0.3498 0.00653 0.00293 -0.1145 0.8550 0.7539
-1.000 0.3772 0.00661 0.00305 -0.1144 0.8536 0.7577
-0.750 0.4051 0.00667 0.00311 -0.1145 0.8519 0.7612
-0.500 0.4340 0.00664 0.00307 -0.1148 0.8494 0.7636
-0.250 0.4644 0.00653 0.00292 -0.1155 0.8463 0.7651
0.000 0.4956 0.00641 0.00276 -0.1163 0.8430 0.7663
0.250 0.5211 0.00636 0.00272 -0.1159 0.8382 0.7676
0.500 0.5487 0.00627 0.00262 -0.1159 0.8325 0.7684
0.750 0.5769 0.00615 0.00249 -0.1161 0.8267 0.7691
1.000 0.6020 0.00608 0.00244 -0.1156 0.8167 0.7698
1.250 0.6270 0.00600 0.00233 -0.1150 0.7984 0.7704
1.500 0.6347 0.00628 0.00216 -0.1105 0.7093 0.7711
1.750 0.6272 0.00704 0.00251 -0.1032 0.6264 0.7721
2.000 0.6294 0.00766 0.00284 -0.0981 0.5587 0.7730
2.250 0.6386 0.00835 0.00322 -0.0947 0.4932 0.7737
2.500 0.6525 0.00893 0.00355 -0.0923 0.4373 0.7743
2.750 0.6701 0.00938 0.00382 -0.0906 0.3939 0.7748
3.000 0.6884 0.00983 0.00408 -0.0891 0.3520 0.7753
3.250 0.7065 0.01031 0.00435 -0.0877 0.3089 0.7758
3.500 0.7246 0.01080 0.00464 -0.0862 0.2638 0.7764
3.750 0.7439 0.01126 0.00492 -0.0849 0.2250 0.7770
4.000 0.7643 0.01166 0.00518 -0.0839 0.1945 0.7777
4.250 0.7846 0.01207 0.00545 -0.0829 0.1648 0.7782
4.500 0.8050 0.01249 0.00573 -0.0819 0.1383 0.7786
4.750 0.8265 0.01284 0.00600 -0.0811 0.1193 0.7791
5.000 0.8482 0.01318 0.00626 -0.0803 0.1039 0.7795
5.250 0.8703 0.01350 0.00652 -0.0796 0.0920 0.7799
5.500 0.8923 0.01383 0.00680 -0.0789 0.0823 0.7804
5.750 0.9141 0.01417 0.00709 -0.0782 0.0734 0.7808
6.000 0.9365 0.01446 0.00737 -0.0775 0.0679 0.7812
6.250 0.9581 0.01480 0.00768 -0.0768 0.0623 0.7816
6.500 0.9805 0.01509 0.00797 -0.0762 0.0592 0.7819
6.750 1.0027 0.01540 0.00828 -0.0755 0.0563 0.7823
7.000 1.0242 0.01574 0.00861 -0.0748 0.0531 0.7827
7.250 1.0455 0.01610 0.00896 -0.0740 0.0502 0.7830
7.500 1.0673 0.01641 0.00930 -0.0734 0.0490 0.7833
7.750 1.0887 0.01675 0.00965 -0.0726 0.0474 0.7837
8.000 1.1095 0.01710 0.01002 -0.0718 0.0454 0.7843
8.250 1.1300 0.01749 0.01042 -0.0710 0.0435 0.7849
8.500 1.1500 0.01791 0.01085 -0.0700 0.0415 0.7855
8.750 1.1704 0.01830 0.01127 -0.0692 0.0406 0.7860
9.000 1.1907 0.01868 0.01170 -0.0683 0.0400 0.7864
9.250 1.2105 0.01909 0.01215 -0.0674 0.0391 0.7869
9.500 1.2301 0.01951 0.01261 -0.0665 0.0381 0.7874
9.750 1.2493 0.01996 0.01309 -0.0655 0.0372 0.7878
10.000 1.2681 0.02044 0.01359 -0.0645 0.0361 0.7883
10.250 1.2860 0.02097 0.01415 -0.0633 0.0349 0.7888
10.500 1.3026 0.02158 0.01479 -0.0620 0.0335 0.7893
10.750 1.3209 0.02207 0.01532 -0.0610 0.0329 0.7898
11.000 1.3394 0.02255 0.01586 -0.0600 0.0322 0.7904
11.250 1.3573 0.02307 0.01642 -0.0589 0.0313 0.7909
11.500 1.3744 0.02363 0.01703 -0.0578 0.0304 0.7914
11.750 1.3908 0.02424 0.01767 -0.0566 0.0294 0.7920
12.000 1.4066 0.02488 0.01834 -0.0553 0.0285 0.7926
12.250 1.4217 0.02558 0.01907 -0.0539 0.0275 0.7931
12.500 1.4362 0.02632 0.01987 -0.0525 0.0267 0.7937
12.750 1.4516 0.02699 0.02060 -0.0513 0.0263 0.7943
13.000 1.4667 0.02769 0.02137 -0.0500 0.0258 0.7948
13.250 1.4816 0.02841 0.02215 -0.0488 0.0250 0.7954
13.500 1.4955 0.02919 0.02297 -0.0475 0.0240 0.7960
13.750 1.5085 0.03003 0.02384 -0.0461 0.0226 0.7965
14.000 1.5210 0.03094 0.02478 -0.0447 0.0214 0.7971
14.250 1.5339 0.03182 0.02573 -0.0434 0.0205 0.7976
14.500 1.5456 0.03280 0.02674 -0.0420 0.0190 0.7981
14.750 1.5561 0.03388 0.02786 -0.0405 0.0176 0.7986
15.000 1.5661 0.03500 0.02905 -0.0390 0.0166 0.7992
15.250 1.5755 0.03620 0.03030 -0.0376 0.0153 0.8000
15.500 1.5830 0.03758 0.03172 -0.0360 0.0138 0.8007
15.750 1.5906 0.03898 0.03319 -0.0345 0.0127 0.8016
16.000 1.5954 0.04064 0.03492 -0.0329 0.0112 0.8024
16.250 1.6004 0.04232 0.03667 -0.0315 0.0103 0.8033
16.500 1.6044 0.04414 0.03857 -0.0300 0.0094 0.8042
16.750 1.6061 0.04624 0.04074 -0.0286 0.0086 0.8050
17.000 1.6091 0.04829 0.04289 -0.0274 0.0081 0.8058
17.250 1.6113 0.05047 0.04517 -0.0263 0.0077 0.8066
17.500 1.6118 0.05286 0.04766 -0.0253 0.0072 0.8074
17.750 1.6111 0.05548 0.05037 -0.0244 0.0069 0.8082
18.000 1.6087 0.05837 0.05336 -0.0237 0.0065 0.8090
18.250 1.6055 0.06146 0.05656 -0.0232 0.0062 0.8098
18.500 1.6030 0.06458 0.05980 -0.0230 0.0060 0.8106
18.750 1.5988 0.06801 0.06334 -0.0230 0.0059 0.8113
19.000 1.5925 0.07176 0.06721 -0.0232 0.0057 0.8121
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Polar data table (+)
Polar graphs
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