RAF 31 AIRFOIL (raf31-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 31 AIRFOIL (raf31-il) Reynolds number: 500,000 Max Cl/Cd: 79.55 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf31-il-500000-n5.txt Download as CSV file: xf-raf31-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8475 0.09192 0.08895 -0.0467 1.0000 0.0166
-16.000 -0.8881 0.08044 0.07730 -0.0536 1.0000 0.0166
-15.750 -0.9162 0.07194 0.06864 -0.0588 1.0000 0.0167
-15.500 -0.9390 0.06469 0.06124 -0.0632 1.0000 0.0167
-15.250 -0.9551 0.05872 0.05512 -0.0669 1.0000 0.0168
-15.000 -0.9663 0.05365 0.04991 -0.0701 1.0000 0.0171
-14.750 -0.9765 0.04896 0.04507 -0.0728 1.0000 0.0173
-14.500 -0.9829 0.04505 0.04103 -0.0750 1.0000 0.0175
-14.250 -0.9888 0.04146 0.03729 -0.0766 1.0000 0.0177
-14.000 -0.9908 0.03860 0.03428 -0.0776 1.0000 0.0181
-13.750 -0.9921 0.03608 0.03160 -0.0781 1.0000 0.0183
-13.500 -0.9922 0.03398 0.02935 -0.0779 1.0000 0.0185
-13.250 -0.9929 0.03212 0.02737 -0.0771 1.0000 0.0188
-13.000 -0.9951 0.03046 0.02564 -0.0755 1.0000 0.0190
-12.750 -0.9949 0.02936 0.02449 -0.0731 1.0000 0.0192
-12.500 -0.9949 0.02853 0.02361 -0.0699 1.0000 0.0195
-12.250 -0.9961 0.02777 0.02279 -0.0660 1.0000 0.0197
-12.000 -0.9888 0.02718 0.02217 -0.0634 1.0000 0.0200
-11.750 -0.9814 0.02646 0.02139 -0.0607 1.0000 0.0204
-11.500 -0.9656 0.02567 0.02051 -0.0597 0.9991 0.0208
-11.250 -0.9376 0.02478 0.01952 -0.0611 0.9960 0.0215
-11.000 -0.9110 0.02395 0.01857 -0.0620 0.9919 0.0221
-10.750 -0.8845 0.02313 0.01763 -0.0628 0.9870 0.0227
-10.500 -0.8586 0.02241 0.01680 -0.0633 0.9812 0.0231
-10.000 -0.8106 0.02068 0.01485 -0.0635 0.9651 0.0240
-9.750 -0.7854 0.01958 0.01369 -0.0640 0.9581 0.0247
-9.500 -0.7566 0.01876 0.01281 -0.0650 0.9514 0.0251
-9.250 -0.7243 0.01802 0.01202 -0.0667 0.9464 0.0257
-9.000 -0.6905 0.01735 0.01128 -0.0686 0.9413 0.0264
-8.750 -0.6556 0.01667 0.01052 -0.0706 0.9365 0.0271
-8.500 -0.6207 0.01600 0.00978 -0.0727 0.9312 0.0276
-8.250 -0.5865 0.01541 0.00910 -0.0745 0.9246 0.0281
-8.000 -0.5526 0.01488 0.00847 -0.0762 0.9174 0.0287
-7.750 -0.5229 0.01443 0.00793 -0.0770 0.9088 0.0291
-7.500 -0.4950 0.01402 0.00743 -0.0773 0.9004 0.0294
-7.250 -0.4694 0.01366 0.00699 -0.0770 0.8918 0.0296
-7.000 -0.4455 0.01324 0.00650 -0.0764 0.8842 0.0299
-6.750 -0.4226 0.01280 0.00598 -0.0757 0.8760 0.0305
-6.500 -0.3991 0.01242 0.00555 -0.0749 0.8690 0.0311
-6.250 -0.3753 0.01210 0.00516 -0.0742 0.8612 0.0318
-6.000 -0.3510 0.01181 0.00482 -0.0736 0.8543 0.0326
-5.750 -0.3266 0.01155 0.00452 -0.0729 0.8467 0.0334
-5.500 -0.3017 0.01132 0.00423 -0.0724 0.8397 0.0343
-5.250 -0.2767 0.01111 0.00396 -0.0718 0.8321 0.0351
-5.000 -0.2514 0.01091 0.00372 -0.0713 0.8246 0.0359
-4.750 -0.2262 0.01073 0.00348 -0.0707 0.8160 0.0368
-4.500 -0.2010 0.01055 0.00326 -0.0701 0.8067 0.0389
-4.250 -0.1761 0.01035 0.00304 -0.0695 0.7970 0.0430
-4.000 -0.1523 0.01004 0.00285 -0.0687 0.7864 0.0674
-3.750 -0.1266 0.00992 0.00269 -0.0683 0.7773 0.0772
-3.500 -0.1012 0.00977 0.00253 -0.0677 0.7681 0.0859
-3.250 -0.0756 0.00964 0.00239 -0.0673 0.7594 0.0947
-2.750 -0.0269 0.00914 0.00208 -0.0660 0.7413 0.1582
-2.500 -0.0023 0.00893 0.00196 -0.0653 0.7331 0.1967
-2.250 0.0225 0.00874 0.00185 -0.0648 0.7239 0.2290
-2.000 0.0470 0.00852 0.00176 -0.0641 0.7159 0.2734
-1.750 0.0718 0.00834 0.00171 -0.0635 0.7074 0.3176
-1.500 0.0973 0.00824 0.00166 -0.0630 0.6997 0.3476
-1.250 0.1230 0.00812 0.00163 -0.0626 0.6924 0.3784
-1.000 0.1482 0.00801 0.00160 -0.0620 0.6855 0.4120
-0.750 0.1737 0.00789 0.00158 -0.0615 0.6781 0.4429
-0.500 0.1985 0.00778 0.00157 -0.0609 0.6712 0.4807
-0.250 0.2241 0.00768 0.00158 -0.0603 0.6641 0.5142
0.000 0.2495 0.00763 0.00159 -0.0598 0.6567 0.5442
0.250 0.2752 0.00757 0.00161 -0.0592 0.6487 0.5708
0.500 0.3003 0.00755 0.00162 -0.0586 0.6394 0.5952
0.750 0.3259 0.00752 0.00165 -0.0580 0.6301 0.6200
1.000 0.3509 0.00749 0.00169 -0.0573 0.6211 0.6445
1.250 0.3753 0.00745 0.00174 -0.0565 0.6107 0.6780
1.500 0.3995 0.00742 0.00180 -0.0556 0.5988 0.7088
1.750 0.4240 0.00744 0.00185 -0.0547 0.5856 0.7317
2.000 0.4483 0.00748 0.00191 -0.0539 0.5693 0.7508
2.250 0.4713 0.00757 0.00197 -0.0528 0.5461 0.7699
2.500 0.4927 0.00771 0.00205 -0.0513 0.5138 0.7897
2.750 0.5133 0.00791 0.00216 -0.0498 0.4801 0.8103
3.000 0.5349 0.00808 0.00229 -0.0484 0.4561 0.8332
3.500 0.5875 0.00838 0.00262 -0.0478 0.4207 0.8948
3.750 0.6345 0.00861 0.00285 -0.0521 0.4025 0.9272
4.000 0.6860 0.00886 0.00307 -0.0574 0.3812 0.9521
4.250 0.7263 0.00913 0.00325 -0.0603 0.3526 0.9737
4.500 0.7548 0.00971 0.00352 -0.0609 0.2853 0.9904
4.750 0.7836 0.01017 0.00383 -0.0615 0.2605 1.0000
5.000 0.8025 0.01047 0.00407 -0.0598 0.2449 1.0000
5.250 0.8221 0.01075 0.00430 -0.0582 0.2285 1.0000
5.500 0.8401 0.01113 0.00454 -0.0563 0.1948 1.0000
5.750 0.8539 0.01174 0.00489 -0.0538 0.1488 1.0000
6.000 0.8707 0.01219 0.00523 -0.0518 0.1273 1.0000
6.250 0.8886 0.01257 0.00556 -0.0499 0.1132 1.0000
6.500 0.9068 0.01294 0.00587 -0.0482 0.1021 1.0000
6.750 0.9249 0.01331 0.00619 -0.0464 0.0930 1.0000
7.000 0.9440 0.01361 0.00649 -0.0448 0.0866 1.0000
7.250 0.9619 0.01398 0.00683 -0.0430 0.0802 1.0000
7.500 0.9810 0.01428 0.00714 -0.0415 0.0757 1.0000
7.750 0.9989 0.01463 0.00748 -0.0397 0.0708 1.0000
8.000 1.0157 0.01498 0.00783 -0.0377 0.0671 1.0000
8.250 1.0324 0.01529 0.00817 -0.0357 0.0639 1.0000
8.500 1.0480 0.01565 0.00853 -0.0335 0.0599 1.0000
8.750 1.0631 0.01606 0.00894 -0.0314 0.0564 1.0000
9.000 1.0798 0.01641 0.00931 -0.0295 0.0523 1.0000
9.250 1.0950 0.01687 0.00975 -0.0275 0.0476 1.0000
9.500 1.1106 0.01731 0.01022 -0.0256 0.0424 1.0000
9.750 1.1246 0.01787 0.01074 -0.0236 0.0351 1.0000
10.000 1.1351 0.01864 0.01143 -0.0212 0.0242 1.0000
10.250 1.1457 0.01944 0.01220 -0.0188 0.0194 1.0000
10.500 1.1575 0.02020 0.01299 -0.0168 0.0173 1.0000
10.750 1.1695 0.02099 0.01381 -0.0148 0.0159 1.0000
11.000 1.1824 0.02174 0.01464 -0.0131 0.0151 1.0000
11.250 1.1941 0.02260 0.01556 -0.0113 0.0141 1.0000
11.500 1.2048 0.02356 0.01656 -0.0096 0.0133 1.0000
11.750 1.2140 0.02466 0.01772 -0.0078 0.0126 1.0000
12.000 1.2245 0.02569 0.01883 -0.0062 0.0122 1.0000
12.250 1.2352 0.02675 0.01996 -0.0048 0.0118 1.0000
12.500 1.2454 0.02786 0.02115 -0.0034 0.0115 1.0000
12.750 1.2542 0.02912 0.02250 -0.0020 0.0111 1.0000
13.000 1.2627 0.03045 0.02391 -0.0007 0.0107 1.0000
13.250 1.2700 0.03191 0.02544 0.0005 0.0105 1.0000
13.500 1.2762 0.03351 0.02713 0.0016 0.0102 1.0000
13.750 1.2805 0.03534 0.02902 0.0027 0.0099 1.0000
14.000 1.2827 0.03741 0.03117 0.0036 0.0096 1.0000
14.250 1.2847 0.03957 0.03343 0.0044 0.0093 1.0000
14.500 1.2883 0.04165 0.03561 0.0050 0.0092 1.0000
14.750 1.2906 0.04392 0.03799 0.0056 0.0090 1.0000
15.000 1.2940 0.04614 0.04031 0.0059 0.0088 1.0000
15.250 1.2947 0.04874 0.04301 0.0061 0.0088 1.0000
15.500 1.2949 0.05147 0.04585 0.0061 0.0085 1.0000
15.750 1.2919 0.05469 0.04918 0.0059 0.0085 1.0000
16.000 1.2906 0.05783 0.05243 0.0055 0.0083 1.0000
16.250 1.2861 0.06149 0.05620 0.0048 0.0082 1.0000
16.500 1.2835 0.06500 0.05982 0.0040 0.0080 1.0000
16.750 1.2779 0.06907 0.06400 0.0029 0.0079 1.0000
17.000 1.2715 0.07339 0.06843 0.0016 0.0078 1.0000
17.250 1.2645 0.07787 0.07303 0.0001 0.0077 1.0000
17.500 1.2557 0.08274 0.07801 -0.0017 0.0077 1.0000
17.750 1.2453 0.08794 0.08333 -0.0037 0.0077 1.0000
18.000 1.2340 0.09340 0.08891 -0.0059 0.0075 1.0000
18.250 1.2226 0.09892 0.09454 -0.0081 0.0076 1.0000
18.500 1.2104 0.10477 0.10051 -0.0107 0.0075 1.0000
18.750 1.1973 0.11091 0.10677 -0.0135 0.0075 1.0000
19.000 1.1841 0.11719 0.11317 -0.0165 0.0074 1.0000
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