FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX74_CL5_140 (fx74cl5140-il) Reynolds number: 500,000 Max Cl/Cd: 115.53 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74cl5140-il-500000-n5.txt Download as CSV file: xf-fx74cl5140-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX74_CL5_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
------ -------- --------- --------- -------- -------- --------
-10.000 0.2873 0.09741 0.09211 -0.1393 0.4967 0.0090
-9.750 0.2964 0.09528 0.08999 -0.1401 0.4956 0.0090
-9.500 0.3044 0.09311 0.08784 -0.1410 0.4947 0.0090
-9.250 0.3138 0.09102 0.08576 -0.1418 0.4935 0.0090
-9.000 0.3220 0.08889 0.08365 -0.1426 0.4924 0.0090
-8.750 0.3308 0.08685 0.08162 -0.1433 0.4911 0.0090
-8.500 0.3419 0.08434 0.07912 -0.1434 0.4899 0.0091
-8.250 0.3522 0.08215 0.07694 -0.1435 0.4886 0.0092
-8.000 0.3612 0.08018 0.07497 -0.1439 0.4874 0.0092
-7.750 0.3700 0.07827 0.07307 -0.1444 0.4862 0.0093
-7.500 0.3786 0.07640 0.07122 -0.1447 0.4850 0.0093
-7.250 0.3867 0.07452 0.06934 -0.1450 0.4840 0.0094
-7.000 0.3947 0.07273 0.06756 -0.1452 0.4828 0.0095
-6.750 0.4020 0.07092 0.06575 -0.1453 0.4816 0.0097
-6.500 0.4088 0.06921 0.06405 -0.1452 0.4803 0.0098
-6.250 0.4146 0.06747 0.06234 -0.1449 0.4793 0.0101
-6.000 0.4189 0.06577 0.06068 -0.1444 0.4784 0.0105
-5.750 0.4216 0.06427 0.05921 -0.1435 0.4776 0.0107
-5.500 0.4282 0.06244 0.05742 -0.1439 0.4767 0.0111
-5.250 0.4375 0.06039 0.05540 -0.1455 0.4759 0.0113
-5.000 0.4496 0.05808 0.05311 -0.1484 0.4750 0.0114
-4.750 0.4667 0.05546 0.05050 -0.1526 0.4740 0.0115
-4.500 0.4835 0.05291 0.04796 -0.1556 0.4729 0.0116
-4.250 0.4960 0.05119 0.04625 -0.1555 0.4719 0.0117
-4.000 0.5154 0.04900 0.04405 -0.1583 0.4709 0.0119
-3.750 0.5397 0.04650 0.04153 -0.1626 0.4698 0.0120
-3.500 0.5687 0.04380 0.03879 -0.1680 0.4688 0.0121
-3.250 0.6024 0.04094 0.03586 -0.1741 0.4677 0.0123
-3.000 0.6410 0.03798 0.03280 -0.1809 0.4666 0.0126
-2.750 0.6844 0.03492 0.02961 -0.1882 0.4655 0.0129
-2.500 0.7326 0.03179 0.02631 -0.1958 0.4643 0.0133
-2.250 0.7936 0.02783 0.02206 -0.2052 0.4633 0.0141
-1.750 0.8886 0.02285 0.01665 -0.2168 0.4615 0.0148
-1.500 0.9312 0.02125 0.01484 -0.2208 0.4605 0.0159
-1.000 1.0200 0.01816 0.01112 -0.2287 0.4583 0.0217
-0.250 0.2622 0.01130 0.00626 0.0203 0.4545 0.0369
0.250 1.1957 0.01500 0.00705 -0.2365 0.4524 0.0159
0.500 1.2267 0.01486 0.00677 -0.2372 0.4513 0.0145
0.750 1.2572 0.01477 0.00664 -0.2379 0.4503 0.0141
1.000 1.2892 0.01463 0.00648 -0.2390 0.4489 0.0138
1.250 1.3209 0.01457 0.00641 -0.2401 0.4476 0.0136
1.500 1.3520 0.01449 0.00635 -0.2410 0.4464 0.0135
1.750 1.3826 0.01446 0.00634 -0.2418 0.4450 0.0135
2.000 1.4125 0.01447 0.00635 -0.2425 0.4436 0.0136
2.250 1.4417 0.01452 0.00638 -0.2430 0.4422 0.0140
2.500 1.4709 0.01459 0.00643 -0.2435 0.4410 0.0150
2.750 1.4994 0.01468 0.00651 -0.2439 0.4399 0.0182
3.000 1.5457 0.01420 0.00710 -0.2488 0.4386 0.6739
3.250 1.5724 0.01436 0.00730 -0.2488 0.4375 0.7210
3.500 1.5987 0.01451 0.00749 -0.2487 0.4363 0.7484
3.750 1.6245 0.01466 0.00769 -0.2485 0.4352 0.7868
4.000 1.6508 0.01484 0.00786 -0.2485 0.4340 0.7925
4.250 1.6772 0.01506 0.00805 -0.2485 0.4328 0.7955
4.500 1.7036 0.01528 0.00827 -0.2486 0.4316 0.7990
4.750 1.7297 0.01543 0.00846 -0.2486 0.4307 0.8028
5.000 1.7556 0.01558 0.00867 -0.2485 0.4295 0.8070
5.250 1.7813 0.01574 0.00887 -0.2485 0.4281 0.8115
5.750 1.8323 0.01609 0.00932 -0.2483 0.4252 0.8227
6.000 1.8573 0.01626 0.00955 -0.2481 0.4238 0.8306
6.250 1.8818 0.01643 0.00978 -0.2479 0.4223 0.8417
6.500 1.9048 0.01658 0.00999 -0.2473 0.4206 0.8606
6.750 1.9190 0.01661 0.01011 -0.2448 0.4190 1.0000
7.000 1.9426 0.01687 0.01037 -0.2445 0.4174 1.0000
7.250 1.9662 0.01712 0.01067 -0.2441 0.4160 1.0000
7.500 1.9895 0.01736 0.01098 -0.2437 0.4146 1.0000
7.750 2.0123 0.01760 0.01129 -0.2433 0.4129 1.0000
8.000 2.0340 0.01786 0.01162 -0.2426 0.4113 1.0000
8.250 2.0549 0.01812 0.01195 -0.2417 0.4097 1.0000
8.500 2.0750 0.01840 0.01229 -0.2408 0.4081 1.0000
8.750 2.0944 0.01870 0.01264 -0.2397 0.4066 1.0000
9.000 2.1133 0.01902 0.01301 -0.2385 0.4051 1.0000
9.250 2.1318 0.01937 0.01340 -0.2373 0.4036 1.0000
9.500 2.1494 0.01974 0.01384 -0.2360 0.4017 1.0000
9.750 2.1668 0.02011 0.01432 -0.2347 0.3989 1.0000
10.000 2.1824 0.02051 0.01480 -0.2330 0.3953 1.0000
10.250 2.1971 0.02097 0.01531 -0.2313 0.3923 1.0000
10.500 2.2088 0.02155 0.01591 -0.2292 0.3887 1.0000
10.750 2.2243 0.02208 0.01657 -0.2277 0.3855 1.0000
11.000 2.2378 0.02270 0.01728 -0.2260 0.3818 1.0000
11.250 2.2488 0.02345 0.01809 -0.2240 0.3779 1.0000
11.500 2.2570 0.02438 0.01906 -0.2217 0.3742 1.0000
11.750 2.2684 0.02522 0.02003 -0.2200 0.3688 1.0000
12.000 2.2721 0.02650 0.02136 -0.2173 0.3615 1.0000
12.250 2.2776 0.02780 0.02274 -0.2151 0.3541 1.0000
12.500 2.2753 0.02969 0.02467 -0.2122 0.3446 1.0000
12.750 2.2674 0.03221 0.02721 -0.2091 0.3323 1.0000
13.000 2.2554 0.03535 0.03038 -0.2060 0.3207 1.0000
13.250 2.2391 0.03922 0.03429 -0.2032 0.3095 1.0000
13.500 2.2176 0.04402 0.03914 -0.2007 0.2984 1.0000
13.750 2.1930 0.04959 0.04477 -0.1986 0.2879 1.0000
14.000 2.1658 0.05589 0.05115 -0.1970 0.2770 1.0000
14.250 2.1357 0.06286 0.05821 -0.1958 0.2680 1.0000
14.500 2.1014 0.07068 0.06609 -0.1948 0.2598 1.0000
14.750 2.0728 0.07793 0.07342 -0.1942 0.2508 1.0000
15.000 2.0422 0.08561 0.08117 -0.1938 0.2400 1.0000
15.250 2.0141 0.09313 0.08871 -0.1937 0.2280 1.0000
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Polar data table (+)
Polar graphs
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