FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 74-CL6-140 (fx74cl6140-il) Reynolds number: 200,000 Max Cl/Cd: 71.99 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74cl6140-il-200000-n5.txt Download as CSV file: xf-fx74cl6140-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-CL6-140
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 0.0410 0.09433 0.08845 -0.0810 0.5332 0.0239
-8.500 0.0483 0.09181 0.08591 -0.0822 0.5315 0.0244
-8.250 0.0542 0.08923 0.08332 -0.0836 0.5299 0.0250
-8.000 0.0569 0.08660 0.08071 -0.0857 0.5285 0.0253
-7.750 0.0609 0.08397 0.07813 -0.0876 0.5267 0.0254
-7.500 0.0647 0.08118 0.07537 -0.0894 0.5251 0.0255
-7.250 0.0748 0.07854 0.07276 -0.0894 0.5230 0.0257
-7.000 0.0859 0.07622 0.07044 -0.0893 0.5210 0.0261
-6.750 0.0935 0.07391 0.06815 -0.0897 0.5193 0.0265
-6.500 0.0987 0.07167 0.06593 -0.0903 0.5177 0.0270
-6.250 0.1030 0.06947 0.06375 -0.0912 0.5163 0.0273
-6.000 0.1109 0.06678 0.06106 -0.0935 0.5149 0.0279
-5.750 0.1211 0.06383 0.05810 -0.0969 0.5136 0.0283
-5.500 0.1359 0.05922 0.05345 -0.1054 0.5124 0.0295
-5.000 0.1738 0.04867 0.04270 -0.1173 0.5099 0.0215
-4.750 0.1932 0.04644 0.04044 -0.1190 0.5081 0.0207
-4.500 0.2192 0.04226 0.03609 -0.1236 0.5064 0.0204
-4.250 0.2509 0.03703 0.03052 -0.1287 0.5047 0.0213
-4.000 0.2800 0.03371 0.02693 -0.1315 0.5028 0.0208
-3.750 0.3122 0.02987 0.02268 -0.1344 0.5011 0.0199
-3.500 0.3469 0.02576 0.01794 -0.1371 0.4996 0.0193
-3.250 0.3793 0.02337 0.01505 -0.1385 0.4981 0.0194
-3.000 0.4104 0.02180 0.01307 -0.1394 0.4967 0.0197
-2.750 0.4408 0.02068 0.01158 -0.1399 0.4953 0.0206
-2.500 0.4705 0.01987 0.01049 -0.1403 0.4938 0.0222
-2.250 0.4993 0.01926 0.00982 -0.1406 0.4921 0.0230
-2.000 0.5282 0.01863 0.00909 -0.1408 0.4902 0.0237
-1.750 0.5571 0.01811 0.00849 -0.1409 0.4883 0.0245
-1.500 0.5861 0.01771 0.00800 -0.1411 0.4865 0.0255
-1.250 0.6152 0.01738 0.00769 -0.1415 0.4849 0.0269
-1.000 0.6444 0.01719 0.00742 -0.1418 0.4834 0.0297
-0.750 0.6737 0.01701 0.00723 -0.1422 0.4819 0.0337
-0.500 0.7032 0.01684 0.00701 -0.1426 0.4804 0.0392
-0.250 0.7329 0.01668 0.00686 -0.1430 0.4790 0.0557
0.000 0.7629 0.01649 0.00686 -0.1437 0.4775 0.1318
0.250 0.7908 0.01547 0.00739 -0.1446 0.4758 0.6429
0.500 0.8165 0.01566 0.00764 -0.1439 0.4742 0.7257
0.750 0.8413 0.01580 0.00782 -0.1430 0.4726 0.7640
1.000 0.8671 0.01594 0.00794 -0.1424 0.4709 0.7888
1.250 0.8915 0.01602 0.00802 -0.1415 0.4691 0.8110
1.500 0.9160 0.01608 0.00808 -0.1407 0.4674 0.8343
1.750 0.9417 0.01616 0.00813 -0.1402 0.4658 0.8477
2.000 0.9700 0.01631 0.00820 -0.1404 0.4644 0.8533
2.250 0.9978 0.01646 0.00828 -0.1405 0.4631 0.8582
2.500 1.0259 0.01663 0.00838 -0.1406 0.4618 0.8638
2.750 1.0530 0.01682 0.00856 -0.1406 0.4602 0.8709
3.000 1.0789 0.01699 0.00879 -0.1404 0.4582 0.8806
3.250 1.1047 0.01715 0.00901 -0.1402 0.4563 0.8939
3.500 1.1309 0.01729 0.00920 -0.1400 0.4546 0.9229
3.750 1.1594 0.01748 0.00940 -0.1404 0.4527 1.0000
4.000 1.1878 0.01772 0.00961 -0.1408 0.4509 1.0000
4.250 1.2162 0.01794 0.00979 -0.1412 0.4492 1.0000
4.500 1.2446 0.01816 0.00998 -0.1416 0.4477 1.0000
4.750 1.2728 0.01841 0.01019 -0.1419 0.4464 1.0000
5.000 1.3012 0.01868 0.01042 -0.1423 0.4451 1.0000
5.250 1.3262 0.01904 0.01088 -0.1422 0.4428 1.0000
5.500 1.3517 0.01938 0.01130 -0.1421 0.4405 1.0000
5.750 1.3776 0.01971 0.01170 -0.1421 0.4385 1.0000
6.000 1.4036 0.02001 0.01203 -0.1422 0.4365 1.0000
6.250 1.4299 0.02026 0.01231 -0.1422 0.4346 1.0000
6.500 1.4565 0.02049 0.01255 -0.1423 0.4329 1.0000
6.750 1.4833 0.02072 0.01279 -0.1424 0.4313 1.0000
7.000 1.5103 0.02098 0.01305 -0.1425 0.4300 1.0000
7.250 1.5333 0.02143 0.01362 -0.1421 0.4277 1.0000
7.500 1.5554 0.02189 0.01423 -0.1416 0.4250 1.0000
7.750 1.5786 0.02228 0.01472 -0.1413 0.4226 1.0000
8.000 1.6025 0.02263 0.01515 -0.1410 0.4205 1.0000
8.250 1.6270 0.02292 0.01551 -0.1408 0.4185 1.0000
8.500 1.6522 0.02315 0.01578 -0.1407 0.4167 1.0000
8.750 1.6781 0.02336 0.01601 -0.1407 0.4150 1.0000
9.000 1.6983 0.02390 0.01671 -0.1399 0.4126 1.0000
9.250 1.7159 0.02454 0.01753 -0.1389 0.4096 1.0000
9.500 1.7355 0.02502 0.01813 -0.1380 0.4068 1.0000
9.750 1.7567 0.02537 0.01859 -0.1374 0.4043 1.0000
10.000 1.7794 0.02564 0.01893 -0.1369 0.4022 1.0000
10.250 1.8036 0.02583 0.01917 -0.1367 0.4003 1.0000
10.500 1.8166 0.02657 0.02010 -0.1350 0.3971 1.0000
10.750 1.8269 0.02736 0.02108 -0.1330 0.3935 1.0000
11.000 1.8413 0.02785 0.02170 -0.1314 0.3902 1.0000
11.250 1.8584 0.02810 0.02203 -0.1301 0.3874 1.0000
11.500 1.8696 0.02849 0.02250 -0.1280 0.3836 1.0000
11.750 1.8600 0.02982 0.02403 -0.1235 0.3780 1.0000
12.000 1.8721 0.02993 0.02415 -0.1217 0.3719 1.0000
12.250 1.8564 0.03211 0.02651 -0.1179 0.3654 1.0000
12.500 1.8593 0.03318 0.02761 -0.1160 0.3578 1.0000
12.750 1.8360 0.03691 0.03152 -0.1135 0.3507 1.0000
13.000 1.8337 0.03904 0.03366 -0.1123 0.3421 1.0000
13.250 1.7957 0.04548 0.04029 -0.1112 0.3345 1.0000
13.500 1.7803 0.04974 0.04460 -0.1108 0.3258 1.0000
13.750 1.7577 0.05508 0.05000 -0.1105 0.3167 1.0000
14.000 1.7250 0.06195 0.05698 -0.1106 0.3079 1.0000
14.250 1.7229 0.06492 0.05996 -0.1103 0.2988 1.0000
14.500 1.7018 0.07063 0.06575 -0.1106 0.2897 1.0000
14.750 1.6909 0.07512 0.07031 -0.1109 0.2812 1.0000
15.000 1.6938 0.07767 0.07286 -0.1109 0.2719 1.0000
15.250 1.6786 0.08301 0.07828 -0.1115 0.2619 1.0000
15.500 1.6719 0.08717 0.08248 -0.1120 0.2516 1.0000
15.750 1.6681 0.09093 0.08627 -0.1125 0.2404 1.0000
16.000 1.6634 0.09486 0.09019 -0.1130 0.2280 1.0000
16.250 1.6566 0.09918 0.09450 -0.1138 0.2148 1.0000
16.500 1.6491 0.10367 0.09896 -0.1146 0.2007 1.0000
16.750 1.6403 0.10840 0.10366 -0.1156 0.1862 1.0000
17.000 1.6307 0.11332 0.10854 -0.1168 0.1717 1.0000
17.250 1.6206 0.11842 0.11359 -0.1182 0.1573 1.0000
17.500 1.6099 0.12366 0.11879 -0.1197 0.1432 1.0000
17.750 1.5996 0.12893 0.12400 -0.1214 0.1290 1.0000
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