WORTMANN FX 082-512 AIRFOIL (fx082512-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 082-512 AIRFOIL (fx082512-il) Reynolds number: 50,000 Max Cl/Cd: 33.45 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx082512-il-50000-n5.txt Download as CSV file: xf-fx082512-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 082-512 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5376 0.10218 0.09477 -0.0503 1.0000 0.0687
-10.750 -0.5620 0.09417 0.08682 -0.0538 1.0000 0.0686
-10.500 -0.5897 0.08655 0.07924 -0.0571 1.0000 0.0682
-10.250 -0.6156 0.08018 0.07287 -0.0596 1.0000 0.0677
-10.000 -0.6433 0.07454 0.06721 -0.0614 1.0000 0.0674
-9.750 -0.6691 0.07003 0.06268 -0.0619 1.0000 0.0671
-9.500 -0.6944 0.06573 0.05833 -0.0627 1.0000 0.0672
-9.250 -0.7108 0.06065 0.05307 -0.0661 1.0000 0.0677
-9.000 -0.7190 0.05514 0.04718 -0.0717 1.0000 0.0693
-8.750 -0.7128 0.05209 0.04400 -0.0725 1.0000 0.0732
-8.500 -0.7038 0.04888 0.04050 -0.0741 1.0000 0.0783
-8.250 -0.6912 0.04635 0.03778 -0.0742 1.0000 0.0835
-8.000 -0.6768 0.04397 0.03519 -0.0749 1.0000 0.0908
-7.750 -0.6609 0.04205 0.03310 -0.0746 1.0000 0.0976
-7.500 -0.6449 0.04045 0.03144 -0.0740 1.0000 0.1055
-7.250 -0.6273 0.03898 0.02988 -0.0736 1.0000 0.1128
-7.000 -0.6117 0.03817 0.02916 -0.0715 1.0000 0.1175
-6.750 -0.5919 0.03686 0.02779 -0.0717 1.0000 0.1247
-6.500 -0.5691 0.03555 0.02638 -0.0728 1.0000 0.1320
-6.250 -0.5456 0.03444 0.02536 -0.0736 1.0000 0.1377
-6.000 -0.5169 0.03305 0.02398 -0.0762 1.0000 0.1469
-5.750 -0.4848 0.03163 0.02271 -0.0798 1.0000 0.1609
-5.500 -0.4627 0.03183 0.02338 -0.0790 1.0000 0.1803
-5.250 -0.4568 0.03430 0.02629 -0.0715 1.0000 0.2023
-5.000 -0.4228 0.03383 0.02549 -0.0748 1.0000 0.2655
-4.500 -0.3599 0.03392 0.02474 -0.0793 1.0000 0.3226
-4.250 -0.3369 0.03439 0.02500 -0.0787 1.0000 0.3365
-4.000 -0.3119 0.03461 0.02498 -0.0789 1.0000 0.3494
-3.750 -0.2967 0.03526 0.02561 -0.0760 1.0000 0.3562
-3.500 -0.2675 0.03492 0.02497 -0.0778 1.0000 0.3656
-3.250 -0.2517 0.03535 0.02540 -0.0753 1.0000 0.3715
-3.000 -0.2225 0.03507 0.02488 -0.0772 1.0000 0.3815
-2.750 -0.2080 0.03549 0.02532 -0.0744 1.0000 0.3873
-2.500 -0.1693 0.03518 0.02472 -0.0785 0.9976 0.3973
-2.250 -0.1447 0.03580 0.02542 -0.0774 0.9930 0.4036
-2.000 -0.1064 0.03567 0.02507 -0.0810 0.9889 0.4141
-1.750 -0.0796 0.03605 0.02550 -0.0807 0.9842 0.4201
-1.500 -0.0450 0.03582 0.02514 -0.0833 0.9795 0.4254
-1.250 -0.0033 0.03540 0.02452 -0.0878 0.9756 0.4285
-1.000 0.0348 0.03502 0.02398 -0.0914 0.9712 0.4304
-0.750 0.0683 0.03483 0.02375 -0.0934 0.9660 0.4318
-0.500 0.1051 0.03476 0.02364 -0.0961 0.9617 0.4338
-0.250 0.1353 0.03462 0.02348 -0.0975 0.9555 0.4362
0.250 0.2094 0.03451 0.02329 -0.1032 0.9455 0.4428
0.500 0.2437 0.03440 0.02312 -0.1057 0.9389 0.4459
0.750 0.2806 0.03441 0.02317 -0.1082 0.9337 0.4480
1.000 0.3124 0.03445 0.02329 -0.1097 0.9270 0.4501
1.250 0.3454 0.03451 0.02342 -0.1114 0.9200 0.4529
1.500 0.3857 0.03459 0.02358 -0.1143 0.9151 0.4567
1.750 0.4142 0.03468 0.02372 -0.1154 0.9057 0.4606
2.000 0.4546 0.03472 0.02386 -0.1182 0.8996 0.4644
2.250 0.4834 0.03477 0.02408 -0.1189 0.8888 0.4673
2.500 0.5242 0.03450 0.02397 -0.1211 0.8772 0.4708
2.750 0.5684 0.03377 0.02337 -0.1234 0.8590 0.4749
3.000 0.6170 0.03262 0.02237 -0.1258 0.8378 0.4803
3.250 0.6607 0.03147 0.02148 -0.1270 0.8188 0.4848
3.500 0.6983 0.03061 0.02086 -0.1275 0.8005 0.4900
3.750 0.7282 0.02999 0.02042 -0.1269 0.7778 0.4950
4.000 0.7657 0.02887 0.01956 -0.1267 0.7534 0.4997
4.250 0.7930 0.02831 0.01924 -0.1254 0.7227 0.5042
4.500 0.8249 0.02763 0.01874 -0.1246 0.6835 0.5103
4.750 0.8643 0.02664 0.01778 -0.1242 0.6081 0.5171
5.000 0.9021 0.02697 0.01672 -0.1233 0.3738 0.5247
5.250 0.9083 0.02897 0.01781 -0.1201 0.2353 0.5300
5.500 0.9202 0.03062 0.01899 -0.1180 0.1738 0.5351
5.750 0.9374 0.03186 0.02014 -0.1165 0.1557 0.5418
6.000 0.9552 0.03310 0.02140 -0.1151 0.1440 0.5490
6.250 0.9734 0.03441 0.02276 -0.1138 0.1345 0.5574
6.500 0.9949 0.03565 0.02413 -0.1128 0.1254 0.5674
6.750 1.0220 0.03710 0.02562 -0.1128 0.1141 0.5802
7.000 1.0599 0.03861 0.02732 -0.1142 0.1013 0.5968
7.250 1.1088 0.04071 0.02966 -0.1174 0.0872 0.6202
7.500 1.1479 0.04288 0.03206 -0.1191 0.0760 0.6527
7.750 1.1785 0.04507 0.03484 -0.1189 0.0685 0.7031
8.000 1.1904 0.04627 0.03641 -0.1158 0.0636 0.8793
8.250 1.2175 0.04927 0.03982 -0.1155 0.0588 1.0000
8.500 1.2398 0.05185 0.04256 -0.1150 0.0548 1.0000
8.750 1.2548 0.05473 0.04579 -0.1133 0.0514 1.0000
9.000 1.2674 0.05781 0.04927 -0.1113 0.0488 1.0000
9.250 1.2808 0.06084 0.05249 -0.1097 0.0473 1.0000
9.500 1.2847 0.06438 0.05644 -0.1069 0.0460 1.0000
9.750 1.2793 0.06815 0.06072 -0.1030 0.0448 1.0000
10.000 1.2716 0.07165 0.06468 -0.0994 0.0437 1.0000
10.250 1.2618 0.07488 0.06820 -0.0958 0.0428 1.0000
10.500 1.2520 0.07812 0.07167 -0.0926 0.0420 1.0000
10.750 1.2418 0.08147 0.07522 -0.0900 0.0414 1.0000
11.000 1.2327 0.08498 0.07886 -0.0880 0.0409 1.0000
11.250 1.2112 0.08957 0.08373 -0.0861 0.0408 1.0000
11.500 1.1892 0.09459 0.08899 -0.0853 0.0409 1.0000
11.750 1.1448 0.10254 0.09737 -0.0868 0.0418 1.0000
12.000 1.1061 0.11164 0.10665 -0.0911 0.0430 1.0000
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Polar data table (+)
Polar graphs
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