FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 74-CL6-140 (fx74cl6140-il) Reynolds number: 500,000 Max Cl/Cd: 120.47 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74cl6140-il-500000-n5.txt Download as CSV file: xf-fx74cl6140-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 0.0515 0.08966 0.08489 -0.0854 0.4916 0.0115
-8.500 0.0571 0.08664 0.08189 -0.0869 0.4905 0.0121
-8.250 0.0560 0.08294 0.07823 -0.0898 0.4895 0.0124
-8.000 0.0628 0.08016 0.07548 -0.0906 0.4882 0.0124
-7.500 0.0828 0.07604 0.07136 -0.0911 0.4853 0.0127
-7.250 0.0901 0.07376 0.06910 -0.0918 0.4841 0.0129
-7.000 0.0956 0.07126 0.06661 -0.0927 0.4829 0.0129
-6.750 0.1009 0.06896 0.06432 -0.0933 0.4818 0.0132
-6.500 0.1028 0.06663 0.06203 -0.0937 0.4806 0.0132
-6.250 0.1077 0.06412 0.05953 -0.0952 0.4795 0.0132
-6.000 0.1236 0.04272 0.03840 -0.0932 0.4767 0.0123
-5.500 0.1398 0.04742 0.04275 -0.1158 0.4767 0.0097
-5.250 0.1615 0.04187 0.03708 -0.1222 0.4757 0.0096
-5.000 0.1892 0.03328 0.02817 -0.1301 0.4747 0.0098
-4.750 0.2178 0.02859 0.02318 -0.1339 0.4734 0.0101
-4.500 0.2476 0.02498 0.01926 -0.1365 0.4721 0.0103
-4.250 0.2793 0.02114 0.01495 -0.1389 0.4708 0.0108
-4.000 0.3114 0.01810 0.01133 -0.1406 0.4694 0.0117
-3.750 0.3422 0.01630 0.00910 -0.1415 0.4681 0.0120
-3.500 0.3721 0.01528 0.00777 -0.1420 0.4667 0.0123
-3.250 0.4014 0.01452 0.00685 -0.1423 0.4654 0.0126
-3.000 0.4303 0.01407 0.00631 -0.1426 0.4640 0.0130
-2.750 0.4592 0.01371 0.00586 -0.1429 0.4625 0.0134
-2.500 0.4881 0.01339 0.00545 -0.1431 0.4609 0.0139
-2.250 0.5174 0.01307 0.00509 -0.1434 0.4598 0.0144
-2.000 0.5467 0.01286 0.00482 -0.1436 0.4586 0.0152
-1.750 0.5760 0.01257 0.00453 -0.1440 0.4574 0.0159
-1.500 0.6054 0.01237 0.00431 -0.1443 0.4561 0.0165
-1.250 0.6347 0.01220 0.00412 -0.1446 0.4547 0.0172
-1.000 0.6640 0.01207 0.00395 -0.1448 0.4533 0.0181
-0.750 0.6932 0.01195 0.00382 -0.1451 0.4518 0.0194
-0.500 0.7223 0.01188 0.00371 -0.1453 0.4503 0.0215
-0.250 0.7513 0.01182 0.00364 -0.1456 0.4490 0.0262
0.000 0.7805 0.01173 0.00359 -0.1459 0.4478 0.0450
0.250 0.8097 0.01165 0.00360 -0.1463 0.4465 0.0884
0.500 0.8388 0.01159 0.00365 -0.1467 0.4450 0.1471
0.750 0.8708 0.01066 0.00385 -0.1485 0.4438 0.5863
1.000 0.8985 0.01070 0.00407 -0.1483 0.4425 0.6932
1.250 0.9265 0.01079 0.00417 -0.1482 0.4412 0.7174
1.500 0.9545 0.01087 0.00425 -0.1482 0.4399 0.7311
1.750 0.9823 0.01096 0.00433 -0.1482 0.4384 0.7456
2.000 1.0101 0.01104 0.00441 -0.1481 0.4369 0.7593
2.250 1.0379 0.01112 0.00448 -0.1481 0.4354 0.7679
2.500 1.0661 0.01122 0.00455 -0.1482 0.4340 0.7709
2.750 1.0942 0.01132 0.00461 -0.1483 0.4327 0.7730
3.000 1.1220 0.01143 0.00470 -0.1484 0.4313 0.7750
3.250 1.1496 0.01157 0.00480 -0.1485 0.4297 0.7776
3.500 1.1776 0.01166 0.00491 -0.1486 0.4284 0.7805
3.750 1.2054 0.01176 0.00504 -0.1487 0.4271 0.7834
4.000 1.2333 0.01186 0.00516 -0.1488 0.4256 0.7862
4.500 1.2884 0.01206 0.00540 -0.1490 0.4221 0.7919
4.750 1.3158 0.01216 0.00554 -0.1491 0.4206 0.7954
5.000 1.3430 0.01228 0.00567 -0.1491 0.4190 0.7996
5.250 1.3702 0.01240 0.00580 -0.1491 0.4174 0.8042
5.500 1.3969 0.01253 0.00595 -0.1491 0.4157 0.8090
5.750 1.4236 0.01269 0.00613 -0.1491 0.4141 0.8146
6.250 1.4770 0.01291 0.00651 -0.1491 0.4108 0.8291
6.500 1.5032 0.01301 0.00670 -0.1490 0.4088 0.8401
6.750 1.5286 0.01310 0.00688 -0.1487 0.4068 0.8584
7.000 1.5525 0.01307 0.00700 -0.1481 0.4051 1.0000
7.250 1.5790 0.01324 0.00720 -0.1481 0.4032 1.0000
7.500 1.6051 0.01343 0.00740 -0.1481 0.4013 1.0000
7.750 1.6310 0.01364 0.00762 -0.1481 0.3994 1.0000
8.000 1.6571 0.01382 0.00789 -0.1481 0.3974 1.0000
8.250 1.6830 0.01401 0.00815 -0.1480 0.3952 1.0000
8.500 1.7085 0.01420 0.00841 -0.1479 0.3928 1.0000
8.750 1.7336 0.01439 0.00865 -0.1478 0.3903 1.0000
9.000 1.7583 0.01460 0.00890 -0.1476 0.3879 1.0000
9.250 1.7825 0.01484 0.00917 -0.1473 0.3856 1.0000
9.500 1.8070 0.01507 0.00949 -0.1470 0.3830 1.0000
9.750 1.8310 0.01529 0.00980 -0.1468 0.3795 1.0000
10.000 1.8535 0.01550 0.01006 -0.1462 0.3740 1.0000
10.250 1.8750 0.01575 0.01035 -0.1455 0.3668 1.0000
10.500 1.8946 0.01606 0.01068 -0.1445 0.3580 1.0000
10.750 1.9138 0.01642 0.01108 -0.1435 0.3481 1.0000
11.000 1.9303 0.01689 0.01156 -0.1421 0.3382 1.0000
11.250 1.9422 0.01750 0.01215 -0.1399 0.3258 1.0000
11.500 1.9474 0.01826 0.01290 -0.1367 0.3121 1.0000
11.750 1.9497 0.01919 0.01382 -0.1332 0.2997 1.0000
12.000 1.9529 0.02018 0.01483 -0.1301 0.2891 1.0000
12.250 1.9527 0.02143 0.01610 -0.1269 0.2790 1.0000
12.500 1.9467 0.02317 0.01787 -0.1236 0.2683 1.0000
12.750 1.9359 0.02554 0.02026 -0.1205 0.2574 1.0000
13.000 1.9218 0.02862 0.02338 -0.1181 0.2460 1.0000
13.250 1.9040 0.03256 0.02737 -0.1163 0.2349 1.0000
13.500 1.8819 0.03742 0.03229 -0.1152 0.2248 1.0000
13.750 1.8551 0.04306 0.03799 -0.1144 0.2150 1.0000
14.000 1.8283 0.04887 0.04385 -0.1137 0.2054 1.0000
14.250 1.8017 0.05473 0.04976 -0.1133 0.1961 1.0000
14.500 1.7753 0.06076 0.05581 -0.1130 0.1866 1.0000
14.750 1.7505 0.06689 0.06196 -0.1132 0.1762 1.0000
15.000 1.7300 0.07270 0.06778 -0.1135 0.1651 1.0000
15.250 1.7116 0.07842 0.07350 -0.1140 0.1534 1.0000
15.500 1.6946 0.08411 0.07919 -0.1147 0.1419 1.0000
15.750 1.6793 0.08969 0.08476 -0.1155 0.1304 1.0000
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Polar data table (+)
Polar graphs
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