S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9026 (9.5%) (s9026-il) Reynolds number: 500,000 Max Cl/Cd: 61.46 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9026-il-500000-n5.txt Download as CSV file: xf-s9026-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9026 (9.5%)
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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.9701 0.13321 0.13057 0.0236 1.0000 0.0087
-16.750 -1.0062 0.12026 0.11750 0.0162 1.0000 0.0086
-16.500 -1.0384 0.10885 0.10594 0.0096 1.0000 0.0085
-16.250 -1.0728 0.09763 0.09458 0.0031 1.0000 0.0084
-16.000 -1.1078 0.08684 0.08363 -0.0032 1.0000 0.0082
-15.750 -1.1409 0.07659 0.07321 -0.0093 1.0000 0.0081
-15.500 -1.1693 0.06734 0.06379 -0.0150 1.0000 0.0080
-15.250 -1.1916 0.05937 0.05565 -0.0201 1.0000 0.0080
-15.000 -1.2104 0.05233 0.04843 -0.0247 1.0000 0.0080
-14.750 -1.2260 0.04634 0.04229 -0.0285 1.0000 0.0081
-14.500 -1.2363 0.04182 0.03761 -0.0309 1.0000 0.0082
-14.250 -1.2430 0.03830 0.03396 -0.0321 1.0000 0.0084
-14.000 -1.2466 0.03558 0.03112 -0.0323 1.0000 0.0085
-13.750 -1.2476 0.03343 0.02885 -0.0317 1.0000 0.0088
-13.500 -1.2457 0.03175 0.02706 -0.0305 1.0000 0.0090
-13.250 -1.2434 0.03027 0.02547 -0.0288 1.0000 0.0093
-13.000 -1.2399 0.02899 0.02407 -0.0266 1.0000 0.0096
-12.750 -1.2334 0.02792 0.02288 -0.0243 1.0000 0.0100
-12.500 -1.2232 0.02685 0.02167 -0.0226 1.0000 0.0104
-12.250 -1.2082 0.02601 0.02070 -0.0213 1.0000 0.0108
-12.000 -1.1962 0.02483 0.01942 -0.0197 1.0000 0.0112
-11.750 -1.1815 0.02381 0.01832 -0.0185 1.0000 0.0118
-11.500 -1.1633 0.02306 0.01751 -0.0175 1.0000 0.0124
-11.250 -1.1444 0.02233 0.01670 -0.0165 1.0000 0.0130
-11.000 -1.1254 0.02157 0.01584 -0.0156 1.0000 0.0136
-10.750 -1.1055 0.02086 0.01503 -0.0146 1.0000 0.0142
-10.500 -1.0845 0.02025 0.01430 -0.0138 1.0000 0.0147
-10.250 -1.0652 0.01940 0.01336 -0.0128 1.0000 0.0154
-10.000 -1.0452 0.01860 0.01249 -0.0119 1.0000 0.0162
-9.750 -1.0237 0.01797 0.01181 -0.0111 1.0000 0.0170
-9.500 -1.0014 0.01741 0.01119 -0.0104 1.0000 0.0179
-9.250 -0.9788 0.01687 0.01058 -0.0096 1.0000 0.0188
-9.000 -0.9560 0.01636 0.00998 -0.0089 1.0000 0.0195
-8.750 -0.9331 0.01583 0.00938 -0.0082 1.0000 0.0202
-8.500 -0.9112 0.01516 0.00867 -0.0073 1.0000 0.0218
-8.250 -0.8881 0.01466 0.00814 -0.0066 1.0000 0.0232
-8.000 -0.8646 0.01420 0.00764 -0.0058 1.0000 0.0246
-7.750 -0.8409 0.01379 0.00717 -0.0051 1.0000 0.0260
-7.500 -0.8175 0.01334 0.00667 -0.0044 1.0000 0.0282
-7.250 -0.7940 0.01292 0.00626 -0.0036 1.0000 0.0313
-7.000 -0.7701 0.01258 0.00589 -0.0029 1.0000 0.0346
-6.750 -0.7468 0.01218 0.00551 -0.0020 1.0000 0.0398
-6.500 -0.7230 0.01188 0.00519 -0.0013 1.0000 0.0442
-6.250 -0.6996 0.01154 0.00485 -0.0004 1.0000 0.0493
-6.000 -0.6759 0.01125 0.00456 0.0004 1.0000 0.0545
-5.750 -0.6524 0.01095 0.00428 0.0013 1.0000 0.0604
-5.500 -0.6288 0.01068 0.00402 0.0021 1.0000 0.0672
-5.250 -0.6055 0.01039 0.00376 0.0030 1.0000 0.0762
-5.000 -0.5823 0.01012 0.00353 0.0039 1.0000 0.0860
-4.750 -0.5537 0.00985 0.00331 0.0036 0.9982 0.0990
-4.500 -0.5187 0.00954 0.00310 0.0020 0.9940 0.1185
-4.250 -0.4852 0.00926 0.00289 0.0007 0.9887 0.1374
-4.000 -0.4499 0.00900 0.00270 -0.0010 0.9834 0.1551
-3.750 -0.4176 0.00876 0.00253 -0.0020 0.9751 0.1743
-3.500 -0.3842 0.00849 0.00236 -0.0032 0.9659 0.1981
-3.250 -0.3507 0.00826 0.00220 -0.0043 0.9535 0.2216
-3.000 -0.3179 0.00804 0.00205 -0.0053 0.9384 0.2448
-2.750 -0.2870 0.00782 0.00191 -0.0059 0.9207 0.2731
-2.500 -0.2588 0.00759 0.00178 -0.0058 0.8994 0.3090
-2.250 -0.2325 0.00742 0.00167 -0.0053 0.8749 0.3409
-2.000 -0.2066 0.00732 0.00156 -0.0046 0.8492 0.3669
-1.750 -0.1810 0.00722 0.00148 -0.0040 0.8231 0.3958
-1.250 -0.1293 0.00704 0.00134 -0.0028 0.7729 0.4563
-1.000 -0.1034 0.00695 0.00128 -0.0023 0.7478 0.4913
-0.500 -0.0519 0.00683 0.00121 -0.0011 0.6877 0.5621
-0.250 -0.0260 0.00682 0.00118 -0.0005 0.6543 0.5920
0.000 0.0000 0.00683 0.00118 0.0000 0.6217 0.6215
0.250 0.0260 0.00682 0.00118 0.0005 0.5919 0.6541
0.500 0.0519 0.00683 0.00121 0.0011 0.5623 0.6878
1.000 0.1034 0.00695 0.00128 0.0023 0.4918 0.7478
1.250 0.1292 0.00704 0.00134 0.0028 0.4560 0.7727
1.750 0.1810 0.00722 0.00148 0.0040 0.3957 0.8233
2.250 0.2324 0.00742 0.00167 0.0053 0.3409 0.8749
2.500 0.2588 0.00759 0.00178 0.0058 0.3089 0.8994
2.750 0.2870 0.00781 0.00191 0.0059 0.2738 0.9207
3.000 0.3179 0.00804 0.00205 0.0053 0.2447 0.9383
3.250 0.3507 0.00826 0.00220 0.0043 0.2216 0.9533
3.500 0.3842 0.00850 0.00236 0.0032 0.1978 0.9659
3.750 0.4176 0.00876 0.00253 0.0020 0.1746 0.9750
4.000 0.4498 0.00900 0.00270 0.0010 0.1553 0.9833
4.250 0.4851 0.00926 0.00289 -0.0006 0.1372 0.9886
4.500 0.5186 0.00954 0.00310 -0.0019 0.1185 0.9940
4.750 0.5535 0.00985 0.00331 -0.0036 0.0987 0.9981
5.000 0.5825 0.01012 0.00353 -0.0040 0.0860 1.0000
5.250 0.6058 0.01039 0.00376 -0.0030 0.0762 1.0000
5.500 0.6290 0.01068 0.00402 -0.0022 0.0672 1.0000
5.750 0.6526 0.01095 0.00428 -0.0013 0.0603 1.0000
6.000 0.6761 0.01125 0.00456 -0.0005 0.0545 1.0000
6.250 0.6998 0.01154 0.00485 0.0004 0.0493 1.0000
6.500 0.7232 0.01188 0.00519 0.0012 0.0441 1.0000
6.750 0.7470 0.01218 0.00551 0.0020 0.0397 1.0000
7.000 0.7702 0.01258 0.00589 0.0028 0.0345 1.0000
7.250 0.7941 0.01292 0.00626 0.0036 0.0313 1.0000
7.500 0.8175 0.01334 0.00668 0.0044 0.0282 1.0000
7.750 0.8409 0.01379 0.00717 0.0051 0.0260 1.0000
8.000 0.8646 0.01420 0.00764 0.0059 0.0246 1.0000
8.250 0.8880 0.01466 0.00814 0.0066 0.0232 1.0000
8.500 0.9110 0.01516 0.00867 0.0073 0.0218 1.0000
8.750 0.9329 0.01583 0.00938 0.0082 0.0202 1.0000
9.000 0.9558 0.01635 0.00997 0.0089 0.0195 1.0000
9.250 0.9787 0.01686 0.01058 0.0097 0.0188 1.0000
9.500 1.0012 0.01740 0.01119 0.0104 0.0179 1.0000
9.750 1.0235 0.01796 0.01181 0.0111 0.0170 1.0000
10.000 1.0450 0.01859 0.01250 0.0119 0.0163 1.0000
10.250 1.0649 0.01941 0.01337 0.0129 0.0154 1.0000
10.500 1.0847 0.02019 0.01424 0.0138 0.0146 1.0000
10.750 1.1052 0.02086 0.01502 0.0147 0.0142 1.0000
11.000 1.1249 0.02159 0.01586 0.0156 0.0136 1.0000
11.250 1.1441 0.02232 0.01669 0.0166 0.0130 1.0000
11.500 1.1630 0.02305 0.01750 0.0175 0.0124 1.0000
11.750 1.1807 0.02384 0.01836 0.0186 0.0119 1.0000
12.000 1.1959 0.02481 0.01940 0.0198 0.0113 1.0000
12.250 1.2087 0.02592 0.02061 0.0213 0.0107 1.0000
12.500 1.2216 0.02693 0.02175 0.0228 0.0105 1.0000
12.750 1.2328 0.02792 0.02288 0.0244 0.0100 1.0000
13.000 1.2386 0.02903 0.02411 0.0268 0.0097 1.0000
13.250 1.2429 0.03027 0.02546 0.0289 0.0093 1.0000
13.500 1.2453 0.03175 0.02706 0.0306 0.0091 1.0000
13.750 1.2463 0.03351 0.02893 0.0318 0.0088 1.0000
14.000 1.2454 0.03566 0.03120 0.0323 0.0086 1.0000
14.250 1.2428 0.03831 0.03397 0.0321 0.0084 1.0000
14.500 1.2354 0.04190 0.03771 0.0309 0.0083 1.0000
14.750 1.2247 0.04653 0.04248 0.0284 0.0082 1.0000
15.000 1.2113 0.05216 0.04827 0.0248 0.0081 1.0000
15.250 1.1924 0.05924 0.05552 0.0201 0.0080 1.0000
15.500 1.1690 0.06744 0.06389 0.0148 0.0080 1.0000
15.750 1.1396 0.07686 0.07349 0.0090 0.0081 1.0000
16.000 1.1083 0.08679 0.08359 0.0031 0.0083 1.0000
16.250 1.0749 0.09736 0.09430 -0.0031 0.0083 1.0000
16.500 1.0394 0.10873 0.10583 -0.0097 0.0085 1.0000
16.750 1.0052 0.12056 0.11780 -0.0165 0.0087 1.0000
17.000 0.9719 0.13294 0.13030 -0.0236 0.0087 1.0000
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Polar data table (+)
Polar graphs
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