FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 74-CL6-140 (fx74cl6140-il) Reynolds number: 1,000,000 Max Cl/Cd: 158.58 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74cl6140-il-1000000-n5.txt Download as CSV file: xf-fx74cl6140-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 0.0583 0.08587 0.08180 -0.0899 0.4710 0.0062
-8.500 0.0655 0.08325 0.07919 -0.0909 0.4698 0.0064
-8.250 0.0720 0.08040 0.07635 -0.0921 0.4688 0.0070
-8.000 0.0784 0.07782 0.07379 -0.0930 0.4676 0.0067
-7.750 0.0846 0.07522 0.07120 -0.0940 0.4665 0.0066
-7.500 0.0881 0.07198 0.06798 -0.0953 0.4655 0.0071
-7.250 0.0948 0.06987 0.06588 -0.0959 0.4643 0.0067
-7.000 0.0977 0.06707 0.06310 -0.0968 0.4631 0.0069
-6.750 0.0976 0.06442 0.06048 -0.0971 0.4619 0.0069
-6.500 0.0993 0.06155 0.05764 -0.0986 0.4609 0.0069
-6.000 0.0968 0.01793 0.01255 -0.1408 0.4613 0.0076
-5.750 0.1253 0.01667 0.01107 -0.1417 0.4603 0.0077
-5.500 0.1540 0.01591 0.01018 -0.1423 0.4592 0.0079
-5.250 0.1829 0.01520 0.00933 -0.1428 0.4580 0.0080
-5.000 0.2119 0.01445 0.00843 -0.1433 0.4568 0.0082
-4.750 0.2410 0.01376 0.00759 -0.1437 0.4556 0.0084
-4.500 0.2701 0.01323 0.00693 -0.1441 0.4543 0.0087
-4.250 0.2992 0.01278 0.00635 -0.1443 0.4530 0.0090
-4.000 0.3283 0.01234 0.00579 -0.1446 0.4516 0.0094
-3.750 0.3575 0.01194 0.00529 -0.1449 0.4502 0.0096
-3.500 0.3865 0.01166 0.00491 -0.1451 0.4487 0.0098
-3.250 0.4158 0.01115 0.00432 -0.1454 0.4470 0.0102
-3.000 0.4447 0.01092 0.00404 -0.1457 0.4453 0.0104
-2.750 0.4740 0.01071 0.00380 -0.1459 0.4445 0.0107
-2.500 0.5033 0.01052 0.00358 -0.1462 0.4437 0.0111
-2.250 0.5326 0.01034 0.00337 -0.1464 0.4428 0.0114
-2.000 0.5620 0.01018 0.00318 -0.1467 0.4417 0.0117
-1.750 0.5913 0.01004 0.00302 -0.1469 0.4404 0.0121
-1.500 0.6205 0.00993 0.00289 -0.1472 0.4390 0.0125
-1.250 0.6499 0.00979 0.00273 -0.1475 0.4377 0.0132
-1.000 0.6791 0.00970 0.00263 -0.1477 0.4364 0.0137
-0.750 0.7082 0.00964 0.00255 -0.1479 0.4352 0.0145
-0.500 0.7372 0.00960 0.00248 -0.1481 0.4339 0.0155
-0.250 0.7662 0.00957 0.00244 -0.1483 0.4324 0.0172
0.000 0.7950 0.00955 0.00241 -0.1485 0.4307 0.0220
0.250 0.8239 0.00951 0.00241 -0.1487 0.4293 0.0382
0.500 0.8533 0.00941 0.00243 -0.1491 0.4285 0.0780
0.750 0.8826 0.00933 0.00245 -0.1495 0.4276 0.1227
1.000 0.9121 0.00920 0.00249 -0.1499 0.4264 0.2021
1.250 0.9436 0.00843 0.00266 -0.1515 0.4251 0.6117
1.500 0.9720 0.00845 0.00279 -0.1515 0.4237 0.6832
1.750 1.0004 0.00852 0.00286 -0.1516 0.4224 0.6977
2.000 1.0288 0.00859 0.00292 -0.1517 0.4210 0.7082
2.250 1.0570 0.00868 0.00299 -0.1518 0.4194 0.7219
2.500 1.0850 0.00875 0.00307 -0.1518 0.4179 0.7311
2.750 1.1131 0.00884 0.00314 -0.1519 0.4164 0.7357
3.000 1.1410 0.00895 0.00322 -0.1520 0.4147 0.7373
3.250 1.1694 0.00902 0.00329 -0.1521 0.4136 0.7389
3.500 1.1977 0.00909 0.00336 -0.1523 0.4124 0.7407
3.750 1.2259 0.00915 0.00345 -0.1524 0.4111 0.7427
4.000 1.2539 0.00922 0.00353 -0.1526 0.4096 0.7447
4.250 1.2819 0.00930 0.00362 -0.1527 0.4080 0.7467
4.500 1.3098 0.00939 0.00371 -0.1528 0.4062 0.7487
4.750 1.3375 0.00948 0.00381 -0.1530 0.4045 0.7508
5.000 1.3651 0.00959 0.00392 -0.1530 0.4029 0.7530
5.250 1.3924 0.00971 0.00403 -0.1531 0.4010 0.7551
5.500 1.4197 0.00983 0.00417 -0.1532 0.3992 0.7575
5.750 1.4474 0.00991 0.00429 -0.1533 0.3978 0.7604
6.000 1.4749 0.00999 0.00441 -0.1534 0.3963 0.7634
6.250 1.5022 0.01009 0.00455 -0.1535 0.3946 0.7664
6.500 1.5294 0.01020 0.00469 -0.1536 0.3925 0.7695
7.000 1.5831 0.01044 0.00498 -0.1537 0.3882 0.7764
7.250 1.6094 0.01059 0.00515 -0.1537 0.3861 0.7808
7.500 1.6361 0.01071 0.00532 -0.1537 0.3842 0.7857
7.750 1.6629 0.01082 0.00549 -0.1538 0.3822 0.7910
8.000 1.6894 0.01093 0.00567 -0.1538 0.3797 0.7978
8.500 1.7412 0.01120 0.00606 -0.1537 0.3743 0.8191
8.750 1.7659 0.01136 0.00628 -0.1534 0.3712 0.8398
9.000 1.7888 0.01128 0.00644 -0.1527 0.3679 1.0000
9.250 1.8137 0.01150 0.00666 -0.1525 0.3605 1.0000
9.500 1.8376 0.01177 0.00692 -0.1522 0.3515 1.0000
9.750 1.8601 0.01212 0.00725 -0.1517 0.3413 1.0000
10.000 1.8813 0.01256 0.00764 -0.1510 0.3286 1.0000
10.250 1.9009 0.01307 0.00810 -0.1500 0.3140 1.0000
10.500 1.9184 0.01370 0.00867 -0.1488 0.2971 1.0000
10.750 1.9324 0.01449 0.00937 -0.1470 0.2773 1.0000
11.000 1.9442 0.01534 0.01014 -0.1449 0.2600 1.0000
11.250 1.9529 0.01621 0.01095 -0.1423 0.2444 1.0000
11.500 1.9529 0.01722 0.01190 -0.1382 0.2271 1.0000
11.750 1.9466 0.01852 0.01314 -0.1334 0.2092 1.0000
12.000 1.9358 0.02019 0.01476 -0.1286 0.1932 1.0000
12.250 1.9217 0.02235 0.01690 -0.1243 0.1792 1.0000
12.500 1.9062 0.02510 0.01966 -0.1209 0.1674 1.0000
12.750 1.8891 0.02862 0.02322 -0.1186 0.1573 1.0000
13.000 1.8689 0.03309 0.02775 -0.1171 0.1483 1.0000
13.250 1.8480 0.03807 0.03279 -0.1162 0.1400 1.0000
13.500 1.8260 0.04333 0.03811 -0.1155 0.1327 1.0000
13.750 1.8015 0.04894 0.04378 -0.1149 0.1259 1.0000
14.000 1.7799 0.05429 0.04919 -0.1145 0.1189 1.0000
14.250 1.7574 0.05988 0.05483 -0.1142 0.1122 1.0000
14.500 1.7386 0.06527 0.06025 -0.1143 0.1041 1.0000
14.750 1.7224 0.07052 0.06551 -0.1146 0.0955 1.0000
15.000 1.7077 0.07574 0.07074 -0.1150 0.0867 1.0000
15.250 1.6934 0.08108 0.07608 -0.1156 0.0779 1.0000
15.500 1.6813 0.08619 0.08119 -0.1163 0.0691 1.0000
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Polar data table (+)
Polar graphs
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