NACA 0018 (naca0018-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0018 (naca0018-il) Reynolds number: 100,000 Max Cl/Cd: 37.49 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0018-il-100000.txt Download as CSV file: xf-naca0018-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0018
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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9550 0.08747 0.08073 -0.0445 1.0000 0.1167
-15.250 -1.0272 0.07547 0.06840 -0.0497 1.0000 0.1161
-15.000 -1.0783 0.06773 0.06033 -0.0516 1.0000 0.1161
-14.750 -1.1189 0.06210 0.05436 -0.0514 1.0000 0.1164
-14.500 -1.1535 0.05778 0.04970 -0.0498 1.0000 0.1169
-14.250 -1.1203 0.05664 0.04877 -0.0500 1.0000 0.1202
-14.000 -1.1217 0.05432 0.04636 -0.0489 1.0000 0.1223
-13.750 -1.1308 0.05169 0.04355 -0.0471 1.0000 0.1244
-13.500 -1.1462 0.04907 0.04066 -0.0443 1.0000 0.1263
-13.250 -1.1656 0.04675 0.03801 -0.0403 1.0000 0.1281
-13.000 -1.1414 0.04522 0.03663 -0.0404 1.0000 0.1320
-12.750 -1.1355 0.04388 0.03523 -0.0383 1.0000 0.1355
-12.500 -1.1414 0.04228 0.03343 -0.0346 1.0000 0.1387
-12.250 -1.1487 0.04066 0.03154 -0.0304 1.0000 0.1418
-12.000 -1.1210 0.03959 0.03072 -0.0308 1.0000 0.1470
-11.750 -1.1195 0.03838 0.02935 -0.0275 1.0000 0.1514
-11.500 -1.1138 0.03697 0.02781 -0.0248 1.0000 0.1561
-11.250 -1.0953 0.03611 0.02710 -0.0236 1.0000 0.1618
-11.000 -1.0950 0.03505 0.02581 -0.0198 1.0000 0.1672
-10.750 -1.0765 0.03402 0.02493 -0.0186 1.0000 0.1734
-10.500 -1.0688 0.03319 0.02403 -0.0157 1.0000 0.1799
-10.250 -1.0581 0.03218 0.02301 -0.0132 1.0000 0.1865
-10.000 -1.0458 0.03148 0.02236 -0.0108 1.0000 0.1937
-9.750 -1.0375 0.03057 0.02136 -0.0079 1.0000 0.2010
-9.500 -1.0236 0.02993 0.02082 -0.0057 1.0000 0.2090
-9.250 -1.0148 0.02910 0.01992 -0.0027 1.0000 0.2172
-9.000 -1.0014 0.02851 0.01944 -0.0004 1.0000 0.2260
-8.750 -0.9907 0.02777 0.01868 0.0023 1.0000 0.2350
-8.500 -0.9790 0.02722 0.01815 0.0050 1.0000 0.2448
-8.250 -0.9660 0.02658 0.01758 0.0074 1.0000 0.2545
-8.000 -0.9568 0.02606 0.01694 0.0104 1.0000 0.2656
-7.750 -0.9410 0.02552 0.01660 0.0123 1.0000 0.2761
-7.500 -0.9288 0.02497 0.01604 0.0149 1.0000 0.2877
-7.250 -0.9162 0.02454 0.01561 0.0173 1.0000 0.3002
-7.000 -0.9009 0.02410 0.01530 0.0193 1.0000 0.3120
-6.750 -0.8871 0.02367 0.01489 0.0215 1.0000 0.3250
-6.500 -0.8738 0.02333 0.01448 0.0238 1.0000 0.3390
-6.250 -0.8569 0.02300 0.01433 0.0255 1.0000 0.3521
-6.000 -0.8409 0.02270 0.01409 0.0272 1.0000 0.3659
-5.750 -0.8252 0.02242 0.01383 0.0290 1.0000 0.3807
-5.500 -0.8096 0.02221 0.01360 0.0307 1.0000 0.3964
-5.250 -0.7920 0.02203 0.01357 0.0322 1.0000 0.4108
-5.000 -0.7748 0.02186 0.01350 0.0336 1.0000 0.4258
-4.750 -0.7579 0.02173 0.01342 0.0350 1.0000 0.4415
-4.500 -0.7326 0.02166 0.01341 0.0348 0.9977 0.4593
-4.250 -0.6863 0.02174 0.01359 0.0308 0.9891 0.4811
-4.000 -0.6394 0.02182 0.01377 0.0268 0.9802 0.5031
-3.750 -0.5975 0.02181 0.01384 0.0238 0.9696 0.5242
-3.500 -0.5556 0.02180 0.01392 0.0209 0.9593 0.5450
-3.250 -0.5079 0.02179 0.01400 0.0171 0.9504 0.5669
-3.000 -0.4718 0.02171 0.01400 0.0155 0.9380 0.5863
-2.750 -0.4314 0.02165 0.01402 0.0133 0.9272 0.6065
-2.500 -0.3860 0.02156 0.01402 0.0103 0.9178 0.6273
-2.250 -0.3503 0.02148 0.01403 0.0092 0.9053 0.6463
-2.000 -0.2985 0.02133 0.01397 0.0054 0.8982 0.6672
-1.750 -0.2642 0.02125 0.01396 0.0047 0.8851 0.6855
-1.500 -0.2136 0.02102 0.01380 0.0015 0.8784 0.7050
-1.250 -0.1834 0.02093 0.01378 0.0019 0.8640 0.7225
-1.000 -0.1421 0.02074 0.01362 0.0005 0.8546 0.7406
-0.750 -0.1085 0.02058 0.01350 0.0005 0.8417 0.7583
-0.500 -0.0739 0.02059 0.01357 0.0005 0.8283 0.7734
-0.250 -0.0290 0.02045 0.01344 -0.0009 0.8185 0.7873
0.000 0.0000 0.02047 0.01348 0.0000 0.8025 0.8025
0.250 0.0290 0.02045 0.01344 0.0009 0.7873 0.8185
0.500 0.0739 0.02059 0.01357 -0.0005 0.7734 0.8283
0.750 0.1085 0.02058 0.01350 -0.0005 0.7583 0.8417
1.000 0.1420 0.02074 0.01362 -0.0005 0.7406 0.8546
1.250 0.1834 0.02093 0.01378 -0.0019 0.7225 0.8640
1.500 0.2136 0.02102 0.01380 -0.0015 0.7050 0.8784
1.750 0.2641 0.02125 0.01396 -0.0047 0.6855 0.8851
2.000 0.2985 0.02133 0.01397 -0.0053 0.6672 0.8982
2.250 0.3503 0.02148 0.01403 -0.0092 0.6464 0.9054
2.500 0.3860 0.02156 0.01402 -0.0103 0.6273 0.9178
2.750 0.4313 0.02165 0.01402 -0.0133 0.6065 0.9273
3.000 0.4718 0.02170 0.01399 -0.0155 0.5863 0.9380
3.250 0.5079 0.02179 0.01399 -0.0171 0.5669 0.9504
3.500 0.5555 0.02180 0.01392 -0.0209 0.5451 0.9594
3.750 0.5975 0.02181 0.01384 -0.0238 0.5242 0.9697
4.000 0.6394 0.02182 0.01376 -0.0268 0.5031 0.9803
4.250 0.6862 0.02173 0.01358 -0.0308 0.4811 0.9891
4.500 0.7326 0.02165 0.01340 -0.0348 0.4594 0.9977
4.750 0.7577 0.02172 0.01341 -0.0350 0.4416 1.0000
5.000 0.7746 0.02186 0.01349 -0.0336 0.4258 1.0000
5.250 0.7917 0.02202 0.01357 -0.0321 0.4109 1.0000
5.500 0.8094 0.02221 0.01359 -0.0307 0.3965 1.0000
5.750 0.8249 0.02241 0.01382 -0.0290 0.3808 1.0000
6.000 0.8406 0.02269 0.01409 -0.0272 0.3659 1.0000
6.250 0.8566 0.02300 0.01432 -0.0254 0.3521 1.0000
6.500 0.8736 0.02332 0.01448 -0.0237 0.3391 1.0000
6.750 0.8869 0.02366 0.01488 -0.0215 0.3250 1.0000
7.000 0.9007 0.02410 0.01530 -0.0193 0.3120 1.0000
7.250 0.9161 0.02454 0.01560 -0.0173 0.3002 1.0000
7.500 0.9286 0.02497 0.01603 -0.0148 0.2878 1.0000
7.750 0.9409 0.02551 0.01659 -0.0123 0.2762 1.0000
8.000 0.9567 0.02605 0.01693 -0.0104 0.2656 1.0000
8.250 0.9659 0.02658 0.01758 -0.0073 0.2545 1.0000
8.500 0.9789 0.02722 0.01815 -0.0050 0.2448 1.0000
8.750 0.9905 0.02777 0.01867 -0.0023 0.2350 1.0000
9.000 1.0013 0.02851 0.01943 0.0004 0.2260 1.0000
9.250 1.0147 0.02910 0.01992 0.0027 0.2172 1.0000
9.500 1.0236 0.02992 0.02082 0.0057 0.2090 1.0000
9.750 1.0375 0.03056 0.02135 0.0079 0.2011 1.0000
10.000 1.0458 0.03148 0.02236 0.0108 0.1937 1.0000
10.250 1.0581 0.03218 0.02300 0.0132 0.1864 1.0000
10.500 1.0689 0.03319 0.02403 0.0157 0.1798 1.0000
10.750 1.0767 0.03402 0.02493 0.0186 0.1734 1.0000
11.000 1.0951 0.03505 0.02581 0.0198 0.1672 1.0000
11.250 1.0956 0.03611 0.02709 0.0236 0.1618 1.0000
11.500 1.1142 0.03697 0.02780 0.0247 0.1561 1.0000
11.750 1.1198 0.03838 0.02935 0.0275 0.1514 1.0000
12.000 1.1215 0.03960 0.03072 0.0307 0.1469 1.0000
12.250 1.1498 0.04067 0.03155 0.0303 0.1417 1.0000
12.500 1.1419 0.04229 0.03344 0.0345 0.1387 1.0000
12.750 1.1362 0.04388 0.03524 0.0382 0.1355 1.0000
13.000 1.1426 0.04522 0.03662 0.0402 0.1320 1.0000
13.250 1.1661 0.04677 0.03803 0.0402 0.1281 1.0000
13.500 1.1468 0.04909 0.04068 0.0442 0.1263 1.0000
13.750 1.1317 0.05171 0.04357 0.0469 0.1243 1.0000
14.000 1.1232 0.05431 0.04635 0.0487 0.1222 1.0000
14.250 1.1226 0.05659 0.04871 0.0498 0.1200 1.0000
14.500 1.1540 0.05783 0.04975 0.0496 0.1169 1.0000
14.750 1.1193 0.06216 0.05444 0.0512 0.1164 1.0000
15.000 1.0788 0.06782 0.06043 0.0513 0.1160 1.0000
15.250 1.0273 0.07564 0.06857 0.0494 0.1161 1.0000
15.500 0.9543 0.08783 0.08110 0.0440 0.1167 1.0000
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