NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il) Reynolds number: 500,000 Max Cl/Cd: 50.39 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0011sc-il-500000-n5.txt Download as CSV file: xf-n0011sc-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA/LANGLEY SYMMETRICAL
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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9413 0.10763 0.10426 -0.0367 1.0000 0.0172
-17.250 -1.0002 0.09207 0.08847 -0.0455 1.0000 0.0171
-17.000 -1.0382 0.08101 0.07721 -0.0520 1.0000 0.0171
-16.750 -1.0675 0.07194 0.06795 -0.0574 1.0000 0.0171
-16.500 -1.0904 0.06451 0.06034 -0.0617 1.0000 0.0171
-16.250 -1.1090 0.05846 0.05409 -0.0647 1.0000 0.0172
-16.000 -1.1243 0.05357 0.04903 -0.0665 1.0000 0.0172
-15.750 -1.1379 0.04945 0.04477 -0.0671 1.0000 0.0173
-15.500 -1.1482 0.04612 0.04130 -0.0668 1.0000 0.0172
-15.250 -1.1590 0.04309 0.03816 -0.0658 1.0000 0.0174
-15.000 -1.1663 0.04063 0.03557 -0.0642 1.0000 0.0174
-14.750 -1.1719 0.03852 0.03334 -0.0621 1.0000 0.0175
-14.500 -1.1754 0.03678 0.03151 -0.0598 1.0000 0.0176
-14.250 -1.1792 0.03508 0.02969 -0.0569 1.0000 0.0176
-14.000 -1.1791 0.03382 0.02836 -0.0541 1.0000 0.0179
-13.750 -1.1795 0.03257 0.02702 -0.0510 1.0000 0.0180
-13.500 -1.1801 0.03134 0.02568 -0.0476 1.0000 0.0180
-13.250 -1.1787 0.03035 0.02461 -0.0442 1.0000 0.0182
-13.000 -1.1765 0.02944 0.02361 -0.0407 1.0000 0.0183
-12.750 -1.1739 0.02860 0.02269 -0.0371 1.0000 0.0185
-12.500 -1.1716 0.02777 0.02177 -0.0333 1.0000 0.0186
-12.250 -1.1689 0.02701 0.02092 -0.0293 1.0000 0.0188
-12.000 -1.1663 0.02627 0.02009 -0.0252 1.0000 0.0189
-11.750 -1.1633 0.02562 0.01936 -0.0211 1.0000 0.0191
-11.500 -1.1578 0.02500 0.01865 -0.0173 0.9998 0.0193
-11.250 -1.1390 0.02423 0.01777 -0.0163 0.9986 0.0195
-11.000 -1.1205 0.02353 0.01698 -0.0152 0.9972 0.0198
-10.750 -1.1006 0.02295 0.01629 -0.0142 0.9958 0.0202
-10.500 -1.0804 0.02231 0.01556 -0.0133 0.9946 0.0205
-10.250 -1.0623 0.02161 0.01483 -0.0120 0.9930 0.0209
-10.000 -1.0422 0.02100 0.01417 -0.0109 0.9912 0.0212
-9.750 -1.0209 0.02047 0.01359 -0.0100 0.9897 0.0216
-9.500 -0.9989 0.01993 0.01300 -0.0093 0.9882 0.0219
-9.250 -0.9754 0.01943 0.01245 -0.0088 0.9869 0.0224
-9.000 -0.9505 0.01893 0.01190 -0.0086 0.9858 0.0229
-8.750 -0.9242 0.01846 0.01136 -0.0087 0.9849 0.0235
-8.500 -0.9029 0.01804 0.01088 -0.0076 0.9831 0.0240
-8.250 -0.8844 0.01754 0.01035 -0.0059 0.9808 0.0245
-8.000 -0.8616 0.01711 0.00992 -0.0051 0.9789 0.0252
-7.750 -0.8364 0.01673 0.00951 -0.0048 0.9773 0.0259
-7.500 -0.8105 0.01636 0.00911 -0.0047 0.9760 0.0267
-7.250 -0.7837 0.01604 0.00875 -0.0047 0.9749 0.0279
-7.000 -0.7566 0.01564 0.00835 -0.0048 0.9740 0.0290
-6.750 -0.7304 0.01532 0.00802 -0.0046 0.9727 0.0303
-6.500 -0.7142 0.01504 0.00772 -0.0022 0.9691 0.0313
-6.250 -0.6903 0.01476 0.00742 -0.0015 0.9669 0.0327
-6.000 -0.6644 0.01442 0.00709 -0.0012 0.9652 0.0343
-5.750 -0.6369 0.01415 0.00682 -0.0013 0.9638 0.0363
-5.500 -0.6086 0.01387 0.00654 -0.0015 0.9627 0.0384
-5.250 -0.5794 0.01359 0.00628 -0.0019 0.9617 0.0416
-5.000 -0.5495 0.01333 0.00604 -0.0025 0.9609 0.0449
-4.750 -0.5370 0.01314 0.00586 0.0008 0.9558 0.0481
-4.500 -0.5120 0.01291 0.00565 0.0014 0.9534 0.0521
-4.250 -0.4845 0.01267 0.00544 0.0014 0.9516 0.0579
-4.000 -0.4558 0.01241 0.00524 0.0011 0.9502 0.0657
-3.750 -0.4260 0.01215 0.00503 0.0007 0.9490 0.0750
-3.500 -0.3956 0.01189 0.00484 0.0000 0.9480 0.0871
-3.250 -0.3767 0.01170 0.00471 0.0020 0.9440 0.0989
-2.750 -0.3280 0.01118 0.00439 0.0035 0.9377 0.1370
-2.500 -0.2992 0.01085 0.00421 0.0032 0.9360 0.1688
-2.250 -0.2693 0.01050 0.00402 0.0027 0.9346 0.2067
-2.000 -0.2392 0.01005 0.00382 0.0021 0.9334 0.2623
-1.750 -0.2284 0.00978 0.00374 0.0058 0.9263 0.3101
-1.500 -0.2063 0.00923 0.00354 0.0070 0.9228 0.3939
-1.250 -0.1846 0.00854 0.00329 0.0083 0.9202 0.5031
-1.000 -0.1640 0.00782 0.00303 0.0099 0.9180 0.6154
-0.750 -0.1644 0.00741 0.00295 0.0165 0.9076 0.6940
-0.500 -0.1231 0.00671 0.00272 0.0142 0.9024 0.8013
-0.250 -0.0682 0.00659 0.00279 0.0087 0.8891 0.8558
0.000 0.0007 0.00662 0.00287 -0.0001 0.8776 0.8781
0.250 0.0664 0.00659 0.00279 -0.0083 0.8564 0.8889
0.500 0.1225 0.00671 0.00273 -0.0140 0.8051 0.9024
0.750 0.1653 0.00738 0.00295 -0.0167 0.7005 0.9075
1.000 0.1647 0.00781 0.00304 -0.0101 0.6168 0.9180
1.250 0.1845 0.00855 0.00329 -0.0082 0.5013 0.9202
1.500 0.2062 0.00924 0.00354 -0.0070 0.3925 0.9228
1.750 0.2282 0.00979 0.00374 -0.0058 0.3079 0.9263
2.000 0.2390 0.01008 0.00383 -0.0020 0.2573 0.9334
2.250 0.2692 0.01050 0.00402 -0.0027 0.2061 0.9346
2.500 0.2988 0.01089 0.00421 -0.0031 0.1629 0.9360
2.750 0.3280 0.01118 0.00439 -0.0035 0.1366 0.9377
3.250 0.3766 0.01170 0.00470 -0.0020 0.0989 0.9440
3.500 0.3957 0.01189 0.00484 -0.0001 0.0872 0.9480
3.750 0.4261 0.01215 0.00503 -0.0007 0.0754 0.9490
4.000 0.4558 0.01241 0.00523 -0.0012 0.0652 0.9502
4.250 0.4846 0.01267 0.00544 -0.0015 0.0578 0.9516
4.500 0.5120 0.01291 0.00564 -0.0014 0.0520 0.9534
4.750 0.5369 0.01315 0.00586 -0.0008 0.0475 0.9559
5.000 0.5495 0.01333 0.00604 0.0025 0.0447 0.9609
5.250 0.5795 0.01359 0.00628 0.0019 0.0413 0.9617
5.500 0.6087 0.01387 0.00654 0.0015 0.0383 0.9627
5.750 0.6370 0.01415 0.00682 0.0013 0.0362 0.9638
6.000 0.6644 0.01443 0.00710 0.0012 0.0342 0.9652
6.250 0.6903 0.01477 0.00742 0.0015 0.0325 0.9670
6.500 0.7143 0.01504 0.00772 0.0022 0.0313 0.9691
6.750 0.7294 0.01531 0.00801 0.0049 0.0301 0.9730
7.000 0.7567 0.01565 0.00835 0.0047 0.0288 0.9740
7.250 0.7841 0.01602 0.00873 0.0046 0.0276 0.9749
7.500 0.8106 0.01637 0.00912 0.0047 0.0267 0.9760
7.750 0.8366 0.01672 0.00950 0.0048 0.0258 0.9773
8.000 0.8617 0.01712 0.00992 0.0051 0.0250 0.9789
8.250 0.8844 0.01755 0.01036 0.0059 0.0243 0.9808
8.500 0.9029 0.01805 0.01089 0.0076 0.0239 0.9832
8.750 0.9246 0.01847 0.01138 0.0086 0.0232 0.9849
9.000 0.9507 0.01895 0.01191 0.0086 0.0228 0.9859
9.250 0.9756 0.01946 0.01248 0.0088 0.0223 0.9870
9.500 0.9991 0.01994 0.01301 0.0092 0.0219 0.9883
9.750 1.0213 0.02047 0.01359 0.0100 0.0215 0.9897
10.000 1.0426 0.02101 0.01417 0.0108 0.0211 0.9913
10.250 1.0624 0.02163 0.01484 0.0119 0.0208 0.9931
10.500 1.0803 0.02237 0.01562 0.0133 0.0205 0.9946
10.750 1.1008 0.02300 0.01634 0.0141 0.0201 0.9959
11.000 1.1204 0.02361 0.01706 0.0151 0.0199 0.9973
11.250 1.1390 0.02430 0.01785 0.0163 0.0196 0.9986
11.500 1.1583 0.02502 0.01866 0.0172 0.0193 0.9999
11.750 1.1631 0.02565 0.01938 0.0211 0.0191 1.0000
12.000 1.1657 0.02634 0.02017 0.0253 0.0190 1.0000
12.250 1.1683 0.02707 0.02098 0.0294 0.0188 1.0000
12.500 1.1721 0.02774 0.02173 0.0332 0.0185 1.0000
12.750 1.1740 0.02862 0.02271 0.0371 0.0185 1.0000
13.000 1.1769 0.02943 0.02360 0.0406 0.0183 1.0000
13.250 1.1784 0.03039 0.02465 0.0442 0.0182 1.0000
13.500 1.1791 0.03146 0.02583 0.0477 0.0181 1.0000
13.750 1.1807 0.03249 0.02693 0.0509 0.0179 1.0000
14.000 1.1811 0.03366 0.02818 0.0539 0.0177 1.0000
14.250 1.1791 0.03514 0.02977 0.0569 0.0177 1.0000
14.500 1.1775 0.03662 0.03133 0.0596 0.0176 1.0000
14.750 1.1723 0.03856 0.03340 0.0621 0.0176 1.0000
15.000 1.1666 0.04068 0.03563 0.0641 0.0175 1.0000
15.250 1.1603 0.04302 0.03808 0.0657 0.0174 1.0000
15.500 1.1495 0.04605 0.04122 0.0667 0.0172 1.0000
15.750 1.1375 0.04958 0.04490 0.0670 0.0172 1.0000
16.000 1.1269 0.05335 0.04881 0.0664 0.0172 1.0000
16.250 1.1087 0.05865 0.05430 0.0645 0.0171 1.0000
16.500 1.0901 0.06467 0.06050 0.0615 0.0171 1.0000
16.750 1.0678 0.07195 0.06795 0.0573 0.0172 1.0000
17.000 1.0394 0.08100 0.07719 0.0518 0.0171 1.0000
17.250 1.0026 0.09182 0.08821 0.0455 0.0172 1.0000
17.500 0.9348 0.10947 0.10616 0.0354 0.0173 1.0000
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