FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 74-130 WP1 (fx74130wp1-il) Reynolds number: 100,000 Max Cl/Cd: 39.65 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74130wp1-il-100000.txt Download as CSV file: xf-fx74130wp1-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-130 WP1
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4279 0.12063 0.11643 -0.0457 0.9867 0.0748
-8.750 -0.4411 0.11811 0.11396 -0.0494 0.9847 0.0753
-8.500 -0.4610 0.11603 0.11195 -0.0500 0.9831 0.0754
-8.250 -0.4334 0.11030 0.10619 -0.0460 0.9821 0.0779
-8.000 -0.4308 0.10782 0.10372 -0.0442 0.9811 0.0802
-7.750 -0.4376 0.10545 0.10139 -0.0433 0.9798 0.0820
-7.500 -0.4496 0.10303 0.09902 -0.0428 0.9785 0.0838
-7.250 -0.4709 0.10118 0.09723 -0.0406 0.9791 0.0842
-7.000 -0.4978 0.09944 0.09556 -0.0378 0.9812 0.0844
-6.750 -0.5714 0.10076 0.09706 -0.0225 1.0000 0.0796
-6.500 -0.5780 0.09772 0.09402 -0.0221 1.0000 0.0812
-6.250 -0.5852 0.09432 0.09060 -0.0224 1.0000 0.0834
-6.000 -0.5914 0.09056 0.08678 -0.0238 1.0000 0.0860
-5.750 -0.6014 0.08758 0.08314 -0.0308 1.0000 0.0898
-5.500 -0.5954 0.08153 0.07747 -0.0277 1.0000 0.0919
-5.250 -0.5895 0.07881 0.07479 -0.0259 1.0000 0.0951
-5.000 -0.5810 0.07489 0.07035 -0.0303 1.0000 0.1050
-4.750 -0.5746 0.07148 0.06717 -0.0276 1.0000 0.1088
-4.500 -0.5607 0.06801 0.06332 -0.0301 1.0000 0.1202
-4.250 -0.5510 0.06522 0.06066 -0.0284 1.0000 0.1274
-4.000 -0.5365 0.06194 0.05721 -0.0294 1.0000 0.1385
-3.750 -0.5206 0.05902 0.05414 -0.0301 1.0000 0.1527
-3.500 -0.5045 0.05645 0.05146 -0.0303 1.0000 0.1690
-3.250 -0.4870 0.05395 0.04880 -0.0310 1.0000 0.1951
-2.500 -0.3747 0.04236 0.03472 -0.0349 1.0000 0.0885
-2.250 -0.3459 0.03910 0.03102 -0.0346 1.0000 0.0708
-2.000 -0.3172 0.03812 0.02928 -0.0336 1.0000 0.0619
-1.750 -0.2926 0.03672 0.02759 -0.0333 1.0000 0.0616
-1.500 -0.2674 0.03501 0.02572 -0.0334 1.0000 0.0636
-1.250 -0.2411 0.03419 0.02478 -0.0334 0.9995 0.0648
-1.000 -0.2100 0.03374 0.02423 -0.0341 0.9976 0.0668
-0.750 -0.1779 0.03374 0.02419 -0.0351 0.9955 0.0718
-0.500 -0.1491 0.03359 0.02412 -0.0359 0.9936 0.0827
-0.250 -0.1172 0.03357 0.02410 -0.0372 0.9900 0.1018
0.000 -0.1153 0.03179 0.02551 -0.0302 0.9924 0.8369
0.250 -0.1089 0.03191 0.02564 -0.0225 0.9831 1.0000
0.500 -0.0761 0.03286 0.02625 -0.0247 0.9751 1.0000
0.750 -0.0491 0.03364 0.02679 -0.0260 0.9680 1.0000
1.000 -0.0139 0.03490 0.02782 -0.0287 0.9608 1.0000
1.250 0.0103 0.03548 0.02822 -0.0295 0.9518 1.0000
1.500 0.0480 0.03708 0.02964 -0.0327 0.9458 1.0000
1.750 0.0700 0.03746 0.02991 -0.0330 0.9352 1.0000
2.000 0.1118 0.03962 0.03190 -0.0370 0.9304 1.0000
2.250 0.1318 0.03969 0.03190 -0.0369 0.9185 1.0000
2.500 0.1550 0.04039 0.03254 -0.0374 0.9081 1.0000
2.750 0.1983 0.04247 0.03451 -0.0415 0.9021 1.0000
3.000 0.2189 0.04277 0.03478 -0.0415 0.8898 1.0000
3.250 0.2428 0.04351 0.03548 -0.0421 0.8778 1.0000
3.500 0.2702 0.04444 0.03638 -0.0432 0.8656 1.0000
3.750 0.3038 0.04535 0.03727 -0.0451 0.8504 1.0000
4.000 0.3870 0.04472 0.03657 -0.0510 0.8046 1.0000
4.250 0.4172 0.04511 0.03698 -0.0519 0.7913 1.0000
4.500 0.4452 0.04553 0.03742 -0.0525 0.7788 1.0000
4.750 0.4740 0.04601 0.03793 -0.0532 0.7677 1.0000
5.000 0.5192 0.04644 0.03844 -0.0560 0.7609 1.0000
5.250 0.5400 0.04684 0.03889 -0.0557 0.7489 1.0000
5.500 0.5645 0.04726 0.03938 -0.0559 0.7377 1.0000
5.750 0.5950 0.04758 0.03978 -0.0567 0.7279 1.0000
6.000 0.6354 0.04761 0.03995 -0.0586 0.7206 1.0000
6.250 0.6594 0.04787 0.04031 -0.0585 0.7088 1.0000
6.500 0.6873 0.04798 0.04054 -0.0588 0.6976 1.0000
6.750 0.7307 0.04743 0.04015 -0.0605 0.6903 1.0000
7.000 0.7663 0.04688 0.03979 -0.0611 0.6801 1.0000
7.250 0.7962 0.04639 0.03947 -0.0611 0.6678 1.0000
7.500 0.8310 0.04539 0.03866 -0.0612 0.6557 1.0000
7.750 0.8987 0.04178 0.03539 -0.0634 0.6503 1.0000
8.000 0.9494 0.03818 0.03208 -0.0632 0.6369 1.0000
8.500 1.0198 0.03200 0.02642 -0.0594 0.5927 1.0000
8.750 1.0426 0.03046 0.02503 -0.0569 0.5512 1.0000
9.000 1.0829 0.02731 0.02080 -0.0536 0.3692 1.0000
9.250 1.0629 0.03030 0.02273 -0.0483 0.2376 1.0000
9.500 1.0473 0.03359 0.02510 -0.0441 0.1487 1.0000
9.750 1.0457 0.03608 0.02720 -0.0413 0.1141 1.0000
10.000 1.0533 0.03805 0.02902 -0.0392 0.0969 1.0000
10.250 1.0700 0.03970 0.03054 -0.0379 0.0849 1.0000
10.500 1.0987 0.04120 0.03187 -0.0378 0.0736 1.0000
10.750 1.1338 0.04259 0.03347 -0.0379 0.0667 1.0000
11.000 1.1845 0.04489 0.03582 -0.0398 0.0588 1.0000
11.250 1.2264 0.04758 0.03886 -0.0410 0.0541 1.0000
11.500 1.2702 0.05239 0.04386 -0.0434 0.0492 1.0000
11.750 1.2800 0.05572 0.04769 -0.0414 0.0485 1.0000
12.000 1.2836 0.05930 0.05171 -0.0391 0.0481 1.0000
12.250 1.2784 0.06262 0.05546 -0.0362 0.0474 1.0000
12.500 1.2686 0.06598 0.05919 -0.0332 0.0467 1.0000
12.750 1.2566 0.06968 0.06324 -0.0305 0.0464 1.0000
13.000 1.2417 0.07365 0.06754 -0.0281 0.0463 1.0000
13.250 1.2246 0.07790 0.07209 -0.0261 0.0464 1.0000
13.500 1.2060 0.08253 0.07699 -0.0246 0.0468 1.0000
13.750 1.1857 0.08748 0.08220 -0.0236 0.0471 1.0000
14.000 1.1653 0.09276 0.08770 -0.0233 0.0476 1.0000
14.250 1.1449 0.09843 0.09357 -0.0236 0.0482 1.0000
14.500 1.1262 0.10454 0.09984 -0.0246 0.0488 1.0000
14.750 0.8779 0.10768 0.10399 -0.0212 0.0562 1.0000
15.000 0.8399 0.11686 0.11330 -0.0271 0.0581 1.0000
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Polar data table (+)
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