FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 77-W-121 (fx77w121-il) Reynolds number: 50,000 Max Cl/Cd: 18.04 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w121-il-50000-n5.txt Download as CSV file: xf-fx77w121-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-121
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3096 0.11476 0.10844 -0.0191 0.7287 0.0993
-9.250 -0.3163 0.11320 0.10688 -0.0229 0.7182 0.1007
-9.000 -0.3217 0.11110 0.10479 -0.0267 0.7089 0.1011
-8.750 -0.2945 0.10492 0.09847 -0.0237 0.6978 0.1038
-8.500 -0.2846 0.10156 0.09505 -0.0242 0.6895 0.1065
-8.250 -0.2812 0.09873 0.09221 -0.0259 0.6823 0.1117
-8.000 -0.2922 0.09682 0.09037 -0.0305 0.6764 0.1151
-7.750 -0.2821 0.09265 0.08618 -0.0304 0.6703 0.1184
-7.500 -0.2714 0.08959 0.08309 -0.0303 0.6637 0.1253
-7.000 -0.2720 0.08367 0.07721 -0.0339 0.6538 0.1348
-6.750 -0.2638 0.08063 0.07412 -0.0349 0.6485 0.1382
-6.500 -0.2574 0.07235 0.06557 -0.0431 0.6460 0.0683
-6.000 -0.2411 0.06348 0.05625 -0.0472 0.6384 0.0564
-5.750 -0.2290 0.06011 0.05277 -0.0474 0.6341 0.0552
-5.500 -0.2167 0.05667 0.04912 -0.0475 0.6306 0.0541
-5.250 -0.2031 0.05334 0.04547 -0.0474 0.6276 0.0532
-5.000 -0.1879 0.05021 0.04206 -0.0473 0.6237 0.0526
-4.750 -0.1716 0.04737 0.03887 -0.0468 0.6201 0.0532
-4.500 -0.1542 0.04468 0.03571 -0.0459 0.6168 0.0548
-4.250 -0.1356 0.04221 0.03265 -0.0447 0.6139 0.0562
-4.000 -0.1152 0.03992 0.02988 -0.0436 0.6103 0.0567
-3.750 -0.0933 0.03793 0.02744 -0.0426 0.6065 0.0572
-3.500 -0.0704 0.03592 0.02510 -0.0419 0.6032 0.0589
-3.250 -0.0466 0.03459 0.02357 -0.0414 0.6003 0.0635
-3.000 -0.0204 0.03324 0.02180 -0.0408 0.5979 0.0674
-2.750 0.0080 0.03199 0.02019 -0.0407 0.5944 0.0701
-2.500 0.0365 0.03092 0.01898 -0.0408 0.5910 0.0753
-2.250 0.0673 0.03012 0.01795 -0.0412 0.5879 0.0837
-2.000 0.1016 0.02920 0.01680 -0.0421 0.5851 0.0905
-1.750 0.1311 0.02865 0.01612 -0.0424 0.5826 0.1051
-1.500 0.1576 0.02829 0.01575 -0.0425 0.5794 0.1211
-1.250 0.2850 0.02444 0.01460 -0.0616 0.5753 1.0000
-1.000 0.3085 0.02482 0.01459 -0.0610 0.5726 1.0000
-0.750 0.3318 0.02517 0.01460 -0.0603 0.5702 1.0000
-0.500 0.3552 0.02560 0.01471 -0.0597 0.5678 1.0000
-0.250 0.3776 0.02627 0.01523 -0.0595 0.5646 1.0000
0.000 0.4000 0.02690 0.01569 -0.0592 0.5618 1.0000
0.250 0.4225 0.02748 0.01607 -0.0587 0.5591 1.0000
0.500 0.4452 0.02799 0.01639 -0.0581 0.5565 1.0000
0.750 0.4682 0.02846 0.01668 -0.0574 0.5543 1.0000
1.000 0.4890 0.02931 0.01745 -0.0571 0.5513 1.0000
1.250 0.5088 0.03030 0.01839 -0.0568 0.5481 1.0000
1.500 0.5291 0.03113 0.01914 -0.0563 0.5449 1.0000
1.750 0.5504 0.03183 0.01974 -0.0557 0.5422 1.0000
2.000 0.5727 0.03240 0.02020 -0.0549 0.5399 1.0000
2.250 0.5914 0.03343 0.02120 -0.0544 0.5368 1.0000
2.500 0.6060 0.03489 0.02269 -0.0540 0.5325 1.0000
2.750 0.6241 0.03588 0.02365 -0.0533 0.5288 1.0000
3.000 0.6451 0.03656 0.02427 -0.0525 0.5260 1.0000
3.250 0.6683 0.03704 0.02469 -0.0516 0.5238 1.0000
3.500 0.6713 0.03953 0.02730 -0.0511 0.5174 1.0000
3.750 0.6875 0.04067 0.02843 -0.0502 0.5135 1.0000
4.000 0.7080 0.04140 0.02914 -0.0493 0.5107 1.0000
4.250 0.7168 0.04321 0.03098 -0.0484 0.5058 1.0000
4.500 0.7215 0.04530 0.03315 -0.0474 0.4997 1.0000
4.750 0.7412 0.04610 0.03394 -0.0465 0.4964 1.0000
5.000 0.7662 0.04646 0.03429 -0.0456 0.4941 1.0000
5.250 0.7483 0.05037 0.03829 -0.0443 0.4842 1.0000
5.500 0.7705 0.05093 0.03886 -0.0434 0.4809 1.0000
6.000 0.7741 0.05537 0.04337 -0.0412 0.4674 1.0000
6.250 0.8011 0.05557 0.04364 -0.0402 0.4648 1.0000
6.750 0.7982 0.06028 0.04842 -0.0377 0.4507 1.0000
7.250 0.8011 0.06457 0.05278 -0.0356 0.4367 1.0000
7.750 0.8089 0.06867 0.05698 -0.0340 0.4227 1.0000
8.250 0.8185 0.07278 0.06125 -0.0326 0.4086 1.0000
8.500 0.8454 0.07295 0.06153 -0.0317 0.4055 1.0000
8.750 0.8294 0.07687 0.06549 -0.0316 0.3948 1.0000
9.000 0.8542 0.07722 0.06599 -0.0307 0.3913 1.0000
9.250 0.8410 0.08108 0.06990 -0.0307 0.3811 1.0000
9.500 0.8636 0.08165 0.07059 -0.0299 0.3776 1.0000
9.750 0.8526 0.08544 0.07444 -0.0301 0.3679 1.0000
10.000 0.8753 0.08591 0.07505 -0.0293 0.3641 1.0000
10.250 0.8644 0.08988 0.07909 -0.0297 0.3548 1.0000
10.500 0.8858 0.09048 0.07983 -0.0289 0.3508 1.0000
10.750 0.8762 0.09445 0.08387 -0.0294 0.3416 1.0000
11.000 0.8957 0.09523 0.08481 -0.0286 0.3373 1.0000
11.250 0.8876 0.09920 0.08890 -0.0292 0.3287 1.0000
11.500 0.9050 0.10014 0.09001 -0.0286 0.3238 1.0000
11.750 0.8996 0.10393 0.09388 -0.0291 0.3157 1.0000
12.000 0.9136 0.10530 0.09542 -0.0287 0.3104 1.0000
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Polar data table (+)
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