FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX74_CL5_140 (fx74cl5140-il) Reynolds number: 1,000,000 Max Cl/Cd: 149.74 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74cl5140-il-1000000-n5.txt Download as CSV file: xf-fx74cl5140-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.3241 0.08973 0.08520 -0.1462 0.4721 0.0068
-9.250 0.3327 0.08772 0.08320 -0.1472 0.4713 0.0068
-9.000 0.3414 0.08555 0.08104 -0.1480 0.4704 0.0068
-8.750 0.3504 0.08350 0.07899 -0.1487 0.4693 0.0068
-8.250 0.3684 0.07910 0.07460 -0.1497 0.4662 0.0068
-8.000 0.3785 0.07707 0.07257 -0.1499 0.4655 0.0069
-7.500 0.3963 0.07328 0.06880 -0.1507 0.4633 0.0069
-7.250 0.4052 0.07146 0.06700 -0.1510 0.4628 0.0070
-7.000 0.4135 0.06963 0.06520 -0.1512 0.4622 0.0070
-6.750 0.4215 0.06787 0.06345 -0.1513 0.4615 0.0071
-6.500 0.4290 0.06622 0.06183 -0.1513 0.4608 0.0073
-6.250 0.4351 0.06453 0.06017 -0.1510 0.4601 0.0075
-6.000 0.4392 0.06297 0.05864 -0.1502 0.4594 0.0079
-5.750 0.4418 0.06151 0.05721 -0.1492 0.4587 0.0079
-5.500 0.4499 0.05967 0.05540 -0.1498 0.4580 0.0084
-5.250 0.4599 0.05762 0.05336 -0.1510 0.4572 0.0088
-5.000 0.4718 0.05532 0.05108 -0.1532 0.4564 0.0089
-4.750 0.4873 0.05284 0.04861 -0.1565 0.4556 0.0089
-4.500 0.5055 0.05034 0.04611 -0.1600 0.4548 0.0089
-4.250 0.5275 0.04765 0.04341 -0.1644 0.4539 0.0090
-4.000 0.5542 0.04472 0.04046 -0.1699 0.4530 0.0090
-3.750 0.5844 0.04171 0.03741 -0.1757 0.4521 0.0090
-3.500 0.6177 0.03871 0.03434 -0.1816 0.4511 0.0090
-3.250 0.6549 0.03560 0.03115 -0.1879 0.4500 0.0090
-3.000 0.6955 0.03252 0.02796 -0.1943 0.4488 0.0090
-2.750 0.7393 0.02943 0.02473 -0.2008 0.4478 0.0090
-2.500 0.7866 0.02630 0.02146 -0.2074 0.4473 0.0090
-2.250 0.8356 0.02326 0.01822 -0.2137 0.4467 0.0090
-2.000 0.8873 0.02026 0.01494 -0.2200 0.4461 0.0090
-1.750 0.9415 0.01734 0.01169 -0.2272 0.4453 0.0092
-1.500 0.9794 0.01634 0.01055 -0.2302 0.4445 0.0095
-1.000 1.0599 0.01429 0.00789 -0.2357 0.4425 0.0117
-0.750 1.0940 0.01362 0.00718 -0.2375 0.4415 0.0122
-0.500 1.1270 0.01320 0.00666 -0.2388 0.4405 0.0129
-0.250 1.1599 0.01284 0.00615 -0.2400 0.4394 0.0149
0.500 1.2543 0.01208 0.00518 -0.2426 0.4351 0.0134
0.750 1.2836 0.01207 0.00508 -0.2429 0.4335 0.0114
1.000 1.3164 0.01185 0.00486 -0.2443 0.4321 0.0109
1.250 1.3482 0.01173 0.00475 -0.2453 0.4314 0.0107
1.500 1.3795 0.01165 0.00467 -0.2463 0.4307 0.0105
1.750 1.4104 0.01161 0.00463 -0.2471 0.4299 0.0105
2.000 1.4406 0.01160 0.00462 -0.2478 0.4290 0.0105
2.250 1.4704 0.01161 0.00463 -0.2484 0.4281 0.0107
2.500 1.4995 0.01164 0.00466 -0.2489 0.4271 0.0112
2.750 1.5283 0.01169 0.00470 -0.2493 0.4260 0.0121
3.000 1.5564 0.01176 0.00477 -0.2496 0.4249 0.0139
3.250 1.5842 0.01184 0.00485 -0.2499 0.4237 0.0166
3.750 1.6570 0.01149 0.00553 -0.2548 0.4212 0.7165
4.000 1.6833 0.01162 0.00570 -0.2547 0.4198 0.7472
4.250 1.7095 0.01177 0.00584 -0.2547 0.4181 0.7495
4.500 1.7356 0.01193 0.00598 -0.2546 0.4165 0.7514
5.000 1.7890 0.01213 0.00623 -0.2548 0.4140 0.7556
5.250 1.8155 0.01225 0.00638 -0.2548 0.4125 0.7577
5.500 1.8416 0.01237 0.00653 -0.2549 0.4109 0.7600
5.750 1.8674 0.01250 0.00668 -0.2548 0.4092 0.7625
6.000 1.8929 0.01265 0.00684 -0.2547 0.4075 0.7651
6.250 1.9181 0.01281 0.00702 -0.2546 0.4059 0.7679
6.500 1.9428 0.01298 0.00721 -0.2544 0.4044 0.7708
6.750 1.9671 0.01317 0.00742 -0.2541 0.4027 0.7742
7.000 1.9922 0.01332 0.00763 -0.2540 0.4014 0.7781
7.250 2.0169 0.01348 0.00784 -0.2538 0.3999 0.7825
7.500 2.0414 0.01365 0.00806 -0.2536 0.3984 0.7873
7.750 2.0654 0.01382 0.00829 -0.2533 0.3967 0.7935
8.250 2.1104 0.01422 0.00879 -0.2521 0.3933 0.8103
8.500 2.1308 0.01446 0.00908 -0.2511 0.3904 0.8250
8.750 2.1517 0.01468 0.00939 -0.2503 0.3873 0.8607
9.250 2.1847 0.01503 0.00993 -0.2468 0.3819 1.0000
9.500 2.2035 0.01537 0.01029 -0.2456 0.3785 1.0000
9.750 2.2194 0.01581 0.01075 -0.2439 0.3745 1.0000
10.000 2.2394 0.01611 0.01111 -0.2430 0.3707 1.0000
10.250 2.2571 0.01651 0.01154 -0.2417 0.3653 1.0000
10.500 2.2705 0.01710 0.01214 -0.2398 0.3598 1.0000
10.750 2.2873 0.01756 0.01264 -0.2384 0.3523 1.0000
11.000 2.2958 0.01844 0.01348 -0.2358 0.3391 1.0000
11.250 2.2953 0.01985 0.01480 -0.2319 0.3211 1.0000
11.500 2.2928 0.02147 0.01637 -0.2279 0.3054 1.0000
11.750 2.2850 0.02353 0.01838 -0.2235 0.2871 1.0000
12.000 2.2709 0.02621 0.02100 -0.2188 0.2676 1.0000
12.250 2.2542 0.02938 0.02414 -0.2144 0.2518 1.0000
12.500 2.2361 0.03305 0.02781 -0.2105 0.2369 1.0000
12.750 2.2092 0.03804 0.03279 -0.2069 0.2208 1.0000
13.000 2.1832 0.04355 0.03835 -0.2042 0.2094 1.0000
13.250 2.1513 0.05032 0.04519 -0.2021 0.1986 1.0000
13.500 2.1197 0.05752 0.05248 -0.2006 0.1907 1.0000
13.750 2.0877 0.06508 0.06013 -0.1995 0.1817 1.0000
14.000 2.0506 0.07356 0.06869 -0.1985 0.1724 1.0000
14.250 2.0194 0.08143 0.07663 -0.1980 0.1643 1.0000
14.500 1.9864 0.08971 0.08494 -0.1977 0.1536 1.0000
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Polar data table (+)
Polar graphs
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