WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Reynolds number: 50,000 Max Cl/Cd: 16.01 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w153-il-50000-n5.txt Download as CSV file: xf-fx77w153-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-W-153 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3304 0.12369 0.11725 -0.0035 0.6996 0.1224
-9.750 -0.3403 0.12139 0.11490 -0.0071 0.6861 0.1265
-9.500 -0.3499 0.11864 0.11211 -0.0109 0.6750 0.1273
-9.250 -0.3318 0.11435 0.10768 -0.0091 0.6580 0.1290
-9.000 -0.3195 0.11095 0.10419 -0.0088 0.6444 0.1311
-8.500 -0.3389 0.09373 0.08683 -0.0259 0.6389 0.0666
-8.250 -0.3270 0.09101 0.08406 -0.0250 0.6278 0.0656
-8.000 -0.3220 0.08722 0.08022 -0.0269 0.6199 0.0641
-7.750 -0.3234 0.08284 0.07581 -0.0298 0.6137 0.0624
-7.250 -0.3401 0.07056 0.06309 -0.0380 0.6066 0.0572
-7.000 -0.3335 0.06698 0.05939 -0.0388 0.6000 0.0567
-6.750 -0.3271 0.06331 0.05550 -0.0394 0.5947 0.0561
-6.500 -0.3196 0.05964 0.05154 -0.0397 0.5900 0.0556
-6.250 -0.3097 0.05605 0.04768 -0.0399 0.5846 0.0552
-6.000 -0.2981 0.05267 0.04393 -0.0396 0.5798 0.0550
-5.750 -0.2845 0.04952 0.04033 -0.0390 0.5757 0.0549
-5.500 -0.2683 0.04659 0.03697 -0.0384 0.5710 0.0552
-5.250 -0.2505 0.04390 0.03376 -0.0377 0.5664 0.0564
-5.000 -0.2308 0.04158 0.03093 -0.0368 0.5623 0.0582
-4.750 -0.2084 0.04018 0.02941 -0.0363 0.5586 0.0606
-4.500 -0.1849 0.03852 0.02742 -0.0359 0.5543 0.0630
-4.250 -0.1602 0.03684 0.02525 -0.0352 0.5501 0.0660
-4.000 -0.1355 0.03565 0.02396 -0.0349 0.5461 0.0699
-3.750 -0.1094 0.03455 0.02250 -0.0343 0.5426 0.0752
-3.500 -0.0824 0.03350 0.02133 -0.0342 0.5388 0.0801
-3.250 -0.0538 0.03255 0.02024 -0.0341 0.5346 0.0846
-3.000 -0.0252 0.03175 0.01933 -0.0341 0.5311 0.0910
-2.750 0.0040 0.03110 0.01854 -0.0341 0.5283 0.0971
-2.500 0.0335 0.03048 0.01778 -0.0341 0.5258 0.1033
-2.000 0.0882 0.02978 0.01705 -0.0343 0.5201 0.1290
-1.750 0.1130 0.02936 0.01679 -0.0341 0.5170 0.1552
-1.500 0.1352 0.02849 0.01655 -0.0336 0.5141 0.2508
-1.250 0.2758 0.02668 0.01669 -0.0512 0.5089 1.0000
-1.000 0.2983 0.02712 0.01689 -0.0510 0.5057 1.0000
-0.750 0.3206 0.02763 0.01721 -0.0508 0.5022 1.0000
-0.500 0.3428 0.02811 0.01748 -0.0504 0.4990 1.0000
-0.250 0.3649 0.02854 0.01770 -0.0498 0.4962 1.0000
0.000 0.3873 0.02896 0.01788 -0.0491 0.4937 1.0000
0.250 0.4098 0.02936 0.01804 -0.0483 0.4916 1.0000
0.500 0.4300 0.03029 0.01896 -0.0482 0.4878 1.0000
0.750 0.4503 0.03111 0.01969 -0.0478 0.4843 1.0000
1.000 0.4710 0.03184 0.02031 -0.0472 0.4815 1.0000
1.250 0.4920 0.03253 0.02088 -0.0465 0.4792 1.0000
1.500 0.5134 0.03317 0.02138 -0.0458 0.4771 1.0000
1.750 0.5353 0.03376 0.02182 -0.0450 0.4752 1.0000
2.000 0.5490 0.03538 0.02352 -0.0446 0.4711 1.0000
2.250 0.5641 0.03671 0.02486 -0.0439 0.4670 1.0000
2.500 0.5819 0.03768 0.02576 -0.0431 0.4638 1.0000
2.750 0.6019 0.03843 0.02641 -0.0422 0.4612 1.0000
3.000 0.6241 0.03897 0.02683 -0.0413 0.4591 1.0000
3.250 0.6258 0.04151 0.02950 -0.0403 0.4531 1.0000
3.500 0.6365 0.04301 0.03099 -0.0392 0.4482 1.0000
3.750 0.6564 0.04365 0.03155 -0.0381 0.4450 1.0000
4.000 0.6804 0.04398 0.03177 -0.0372 0.4427 1.0000
4.500 0.6701 0.05000 0.03796 -0.0348 0.4306 1.0000
4.750 0.6903 0.05070 0.03859 -0.0338 0.4279 1.0000
5.000 0.7071 0.05175 0.03959 -0.0328 0.4249 1.0000
5.500 0.6863 0.05885 0.04678 -0.0312 0.4116 1.0000
5.750 0.7098 0.05937 0.04726 -0.0303 0.4098 1.0000
6.250 0.6708 0.06824 0.05617 -0.0297 0.3953 1.0000
6.500 0.6575 0.07218 0.06011 -0.0296 0.3882 1.0000
6.750 0.6598 0.07473 0.06266 -0.0293 0.3826 1.0000
7.000 0.6788 0.07578 0.06370 -0.0287 0.3795 1.0000
7.250 0.7007 0.07658 0.06447 -0.0280 0.3770 1.0000
7.500 0.6741 0.08185 0.06980 -0.0287 0.3674 1.0000
7.750 0.6916 0.08310 0.07103 -0.0282 0.3642 1.0000
8.000 0.7156 0.08373 0.07165 -0.0274 0.3620 1.0000
8.250 0.6890 0.08922 0.07719 -0.0284 0.3530 1.0000
8.500 0.7021 0.09098 0.07896 -0.0282 0.3496 1.0000
8.750 0.7204 0.09230 0.08031 -0.0277 0.3473 1.0000
9.000 0.7082 0.09676 0.08482 -0.0286 0.3419 1.0000
9.250 0.7067 0.10012 0.08822 -0.0290 0.3374 1.0000
9.500 0.7188 0.10207 0.09019 -0.0289 0.3340 1.0000
9.750 0.7386 0.10325 0.09140 -0.0285 0.3316 1.0000
10.000 0.7253 0.10768 0.09587 -0.0294 0.3253 1.0000
10.250 0.7290 0.11056 0.09880 -0.0298 0.3215 1.0000
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