RAF 31 AIRFOIL (raf31-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 31 AIRFOIL (raf31-il) Reynolds number: 100,000 Max Cl/Cd: 52.95 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf31-il-100000.txt Download as CSV file: xf-raf31-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 31 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4213 0.09671 0.09145 -0.0354 1.0000 0.1761
-9.250 -0.4751 0.09277 0.08776 -0.0407 1.0000 0.1851
-9.000 -0.6444 0.06198 0.05675 -0.0550 1.0000 0.0945
-8.750 -0.6559 0.05866 0.05340 -0.0522 1.0000 0.0929
-8.500 -0.6748 0.05526 0.04988 -0.0486 1.0000 0.0913
-8.250 -0.6945 0.05151 0.04587 -0.0449 1.0000 0.0893
-8.000 -0.7119 0.04726 0.04118 -0.0411 1.0000 0.0868
-7.750 -0.7270 0.04313 0.03627 -0.0370 1.0000 0.0844
-7.500 -0.7234 0.04066 0.03340 -0.0342 1.0000 0.0838
-7.250 -0.7160 0.03837 0.03074 -0.0317 1.0000 0.0835
-7.000 -0.7059 0.03614 0.02819 -0.0296 1.0000 0.0835
-6.750 -0.6937 0.03396 0.02575 -0.0278 1.0000 0.0840
-6.500 -0.6795 0.03220 0.02385 -0.0262 1.0000 0.0856
-6.250 -0.6638 0.03092 0.02244 -0.0247 1.0000 0.0878
-6.000 -0.6475 0.02968 0.02101 -0.0232 1.0000 0.0898
-5.750 -0.6301 0.02841 0.01951 -0.0217 1.0000 0.0915
-5.500 -0.6120 0.02728 0.01816 -0.0202 1.0000 0.0933
-5.250 -0.5935 0.02635 0.01699 -0.0188 1.0000 0.0955
-5.000 -0.5751 0.02510 0.01576 -0.0176 1.0000 0.0989
-4.750 -0.5434 0.02430 0.01499 -0.0189 0.9962 0.1061
-4.500 -0.5098 0.02334 0.01406 -0.0203 0.9914 0.1143
-4.250 -0.4784 0.02239 0.01325 -0.0215 0.9862 0.1300
-4.000 -0.4492 0.02136 0.01257 -0.0223 0.9814 0.1734
-3.750 -0.4213 0.02043 0.01217 -0.0232 0.9751 0.2521
-3.500 -0.3903 0.02005 0.01225 -0.0244 0.9687 0.3578
-3.250 -0.3594 0.01994 0.01238 -0.0253 0.9612 0.4313
-3.000 -0.3284 0.01994 0.01254 -0.0261 0.9534 0.4882
-2.750 -0.2920 0.02004 0.01278 -0.0276 0.9456 0.5443
-2.500 -0.2639 0.02007 0.01290 -0.0275 0.9364 0.5879
-2.250 -0.2233 0.02015 0.01305 -0.0295 0.9299 0.6338
-2.000 -0.2016 0.02017 0.01316 -0.0282 0.9209 0.6692
-1.750 -0.1663 0.02026 0.01333 -0.0291 0.9155 0.7120
-1.500 -0.1461 0.02034 0.01351 -0.0273 0.9076 0.7500
-1.250 -0.1133 0.02036 0.01361 -0.0276 0.9015 0.7949
-1.000 -0.0811 0.02038 0.01372 -0.0278 0.8950 0.8385
-0.750 -0.0371 0.02042 0.01383 -0.0303 0.8887 0.8862
-0.500 0.0410 0.02061 0.01398 -0.0395 0.8860 0.9268
-0.250 0.1291 0.02081 0.01407 -0.0507 0.8846 0.9553
0.000 0.2169 0.02077 0.01393 -0.0621 0.8835 0.9717
0.250 0.2861 0.02070 0.01380 -0.0707 0.8765 0.9905
0.500 0.3638 0.02019 0.01324 -0.0804 0.8723 1.0000
0.750 0.3794 0.02005 0.01306 -0.0791 0.8604 1.0000
1.000 0.4208 0.01960 0.01258 -0.0817 0.8531 1.0000
1.250 0.4278 0.01966 0.01259 -0.0784 0.8397 1.0000
1.500 0.4439 0.01967 0.01257 -0.0765 0.8277 1.0000
1.750 0.4859 0.01928 0.01216 -0.0786 0.8209 1.0000
2.000 0.5016 0.01935 0.01220 -0.0763 0.8077 1.0000
2.250 0.5238 0.01931 0.01214 -0.0749 0.7956 1.0000
2.500 0.5655 0.01886 0.01169 -0.0766 0.7887 1.0000
2.750 0.5834 0.01897 0.01181 -0.0746 0.7755 1.0000
3.000 0.6054 0.01899 0.01183 -0.0731 0.7628 1.0000
3.250 0.6324 0.01885 0.01171 -0.0723 0.7507 1.0000
3.500 0.6703 0.01842 0.01127 -0.0731 0.7415 1.0000
3.750 0.6918 0.01848 0.01135 -0.0715 0.7275 1.0000
4.000 0.7162 0.01839 0.01128 -0.0702 0.7129 1.0000
4.250 0.7429 0.01814 0.01103 -0.0690 0.6971 1.0000
4.500 0.7704 0.01780 0.01066 -0.0679 0.6797 1.0000
4.750 0.7965 0.01755 0.01039 -0.0666 0.6618 1.0000
5.000 0.8155 0.01752 0.01038 -0.0643 0.6416 1.0000
5.250 0.8369 0.01743 0.01030 -0.0623 0.6215 1.0000
5.500 0.8598 0.01732 0.01016 -0.0607 0.6011 1.0000
5.750 0.8797 0.01736 0.01023 -0.0586 0.5801 1.0000
6.000 0.8987 0.01741 0.01029 -0.0564 0.5566 1.0000
6.250 0.9171 0.01750 0.01037 -0.0542 0.5311 1.0000
6.500 0.9348 0.01766 0.01048 -0.0518 0.5026 1.0000
6.750 0.9500 0.01794 0.01067 -0.0490 0.4691 1.0000
7.000 0.9625 0.01841 0.01095 -0.0458 0.4295 1.0000
7.250 0.9689 0.01904 0.01142 -0.0417 0.3782 1.0000
7.500 0.9671 0.01992 0.01192 -0.0364 0.3038 1.0000
7.750 0.9648 0.02147 0.01287 -0.0316 0.2525 1.0000
8.000 0.9720 0.02280 0.01397 -0.0283 0.2194 1.0000
8.250 0.9826 0.02383 0.01484 -0.0256 0.1994 1.0000
8.500 0.9963 0.02486 0.01574 -0.0234 0.1851 1.0000
8.750 1.0138 0.02597 0.01677 -0.0219 0.1731 1.0000
9.000 1.0344 0.02720 0.01795 -0.0209 0.1620 1.0000
9.250 1.0543 0.02850 0.01916 -0.0200 0.1507 1.0000
9.500 1.0718 0.02982 0.02035 -0.0190 0.1385 1.0000
9.750 1.0830 0.03082 0.02145 -0.0167 0.1286 1.0000
10.000 1.1002 0.03226 0.02297 -0.0154 0.1188 1.0000
10.250 1.1193 0.03395 0.02463 -0.0147 0.1081 1.0000
10.500 1.1378 0.03584 0.02643 -0.0140 0.0967 1.0000
10.750 1.1406 0.03715 0.02803 -0.0104 0.0888 1.0000
11.000 1.1560 0.03938 0.03032 -0.0092 0.0802 1.0000
11.250 1.1658 0.04089 0.03188 -0.0071 0.0742 1.0000
11.500 1.1791 0.04346 0.03466 -0.0057 0.0695 1.0000
11.750 1.1849 0.04568 0.03717 -0.0032 0.0662 1.0000
12.000 1.1935 0.04765 0.03923 -0.0014 0.0632 1.0000
12.250 1.2076 0.05090 0.04254 -0.0008 0.0605 1.0000
12.500 1.1960 0.05326 0.04529 0.0031 0.0595 1.0000
12.750 1.1834 0.05592 0.04829 0.0063 0.0584 1.0000
13.000 1.1701 0.05892 0.05161 0.0089 0.0575 1.0000
13.250 1.1548 0.06232 0.05529 0.0110 0.0567 1.0000
13.500 1.1373 0.06619 0.05943 0.0124 0.0565 1.0000
13.750 1.1158 0.07057 0.06408 0.0132 0.0564 1.0000
14.000 1.0904 0.07563 0.06941 0.0131 0.0564 1.0000
14.250 1.0608 0.08164 0.07566 0.0119 0.0568 1.0000
14.500 1.0286 0.08858 0.08283 0.0094 0.0574 1.0000
14.750 0.9965 0.09644 0.09086 0.0056 0.0584 1.0000
15.000 0.9614 0.10591 0.10048 0.0004 0.0594 1.0000
15.250 0.9316 0.11576 0.11041 -0.0052 0.0602 1.0000
15.500 0.9129 0.12455 0.11924 -0.0096 0.0609 1.0000
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