FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 78-K-140 A/20 (fx78k140a20-il) Reynolds number: 200,000 Max Cl/Cd: 54.64 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx78k140a20-il-200000.txt Download as CSV file: xf-fx78k140a20-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 78-K-140 A/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1015 0.10816 0.10380 -0.1150 0.8168 0.0401
-11.250 -0.1018 0.10539 0.10108 -0.1175 0.8157 0.0404
-11.000 -0.1009 0.10228 0.09800 -0.1196 0.8146 0.0406
-10.750 -0.0983 0.09908 0.09483 -0.1213 0.8133 0.0407
-10.500 -0.0968 0.09329 0.08908 -0.1212 0.8122 0.0417
-10.250 -0.0837 0.09075 0.08651 -0.1201 0.8109 0.0430
-10.000 -0.0786 0.08807 0.08383 -0.1206 0.8098 0.0438
-9.750 -0.0743 0.08558 0.08136 -0.1210 0.8088 0.0453
-9.500 -0.0735 0.08286 0.07867 -0.1219 0.8077 0.0457
-9.250 -0.0751 0.07984 0.07571 -0.1227 0.8065 0.0471
-9.000 -0.0775 0.07691 0.07284 -0.1238 0.8052 0.0477
-8.750 -0.0877 0.07320 0.06921 -0.1257 0.8036 0.0499
-8.500 -0.1053 0.06938 0.06545 -0.1282 0.8013 0.0512
-8.250 -0.1177 0.06680 0.06290 -0.1275 0.7996 0.0511
-8.000 -0.1488 0.06514 0.06110 -0.1249 0.7979 0.0527
-7.750 -0.1614 0.06394 0.05970 -0.1224 0.7964 0.0531
-7.500 -0.1707 0.06225 0.05783 -0.1196 0.7944 0.0534
-7.250 -0.1794 0.05669 0.05228 -0.1182 0.7925 0.0545
-7.000 -0.1718 0.05386 0.04950 -0.1172 0.7909 0.0555
-6.750 -0.1646 0.05184 0.04745 -0.1157 0.7893 0.0570
-6.500 -0.1589 0.04996 0.04548 -0.1138 0.7877 0.0592
-6.250 -0.1530 0.04791 0.04323 -0.1116 0.7857 0.0614
-6.000 -0.1572 0.04072 0.03519 -0.1060 0.7842 0.0380
-5.750 -0.1598 0.03572 0.02948 -0.1010 0.7822 0.0318
-5.500 -0.1484 0.03532 0.02907 -0.0994 0.7798 0.0339
-5.250 -0.1374 0.03380 0.02725 -0.0969 0.7771 0.0344
-5.000 -0.1221 0.03243 0.02556 -0.0948 0.7749 0.0363
-4.750 -0.1033 0.03084 0.02360 -0.0930 0.7733 0.0369
-4.500 -0.0803 0.02958 0.02201 -0.0917 0.7720 0.0391
-4.250 -0.0555 0.02833 0.02055 -0.0911 0.7708 0.0435
-4.000 -0.0534 0.02854 0.02079 -0.0878 0.7663 0.0463
-3.750 -0.0424 0.02840 0.02057 -0.0853 0.7634 0.0498
-3.500 -0.0241 0.02788 0.01996 -0.0838 0.7611 0.0562
-3.250 0.0004 0.02745 0.01949 -0.0832 0.7592 0.0656
-3.000 0.0255 0.02684 0.01889 -0.0825 0.7578 0.0786
-2.750 0.0500 0.02639 0.01846 -0.0818 0.7567 0.0971
-2.500 0.0190 0.02793 0.02001 -0.0737 0.7485 0.0954
-2.250 0.0375 0.02762 0.01981 -0.0723 0.7462 0.1240
-2.000 0.0561 0.02691 0.01960 -0.0708 0.7447 0.2211
-1.750 0.0348 0.02749 0.02056 -0.0634 0.7384 0.3097
-1.500 0.0174 0.02700 0.02107 -0.0559 0.7336 0.5517
-1.250 0.0158 0.02700 0.02206 -0.0476 0.7314 0.8730
-1.000 0.0509 0.02720 0.02218 -0.0465 0.7303 0.9304
-0.750 0.4528 0.02619 0.02035 -0.1143 0.7435 0.9905
-0.500 0.5035 0.02661 0.02072 -0.1209 0.7400 1.0000
-0.250 0.5031 0.02746 0.02156 -0.1172 0.7344 1.0000
0.000 0.5219 0.02763 0.02167 -0.1159 0.7319 1.0000
0.250 0.5452 0.02767 0.02165 -0.1152 0.7303 1.0000
0.500 0.5716 0.02765 0.02156 -0.1149 0.7291 1.0000
0.750 0.5403 0.02942 0.02339 -0.1069 0.7187 1.0000
1.000 0.5661 0.02938 0.02330 -0.1064 0.7170 1.0000
1.250 0.5945 0.02929 0.02316 -0.1064 0.7158 1.0000
1.500 0.5541 0.03111 0.02502 -0.0967 0.7048 1.0000
1.750 0.5826 0.03103 0.02492 -0.0967 0.7032 1.0000
2.000 0.6145 0.03084 0.02470 -0.0971 0.7021 1.0000
2.250 0.6474 0.03064 0.02447 -0.0977 0.7012 1.0000
2.500 0.6015 0.03222 0.02609 -0.0868 0.6892 1.0000
2.750 0.6367 0.03199 0.02584 -0.0878 0.6882 1.0000
3.000 0.5775 0.03332 0.02717 -0.0743 0.6760 1.0000
3.250 0.5407 0.03436 0.02820 -0.0647 0.6657 1.0000
3.500 0.5670 0.03421 0.02805 -0.0642 0.6633 1.0000
3.750 0.5994 0.03394 0.02778 -0.0646 0.6619 1.0000
4.000 0.6343 0.03366 0.02753 -0.0654 0.6610 1.0000
4.250 0.6098 0.03480 0.02866 -0.0584 0.6495 1.0000
4.500 0.6427 0.03453 0.02842 -0.0589 0.6482 1.0000
4.750 0.6367 0.03573 0.02963 -0.0552 0.6381 1.0000
5.000 0.6667 0.03559 0.02954 -0.0555 0.6360 1.0000
5.250 0.7005 0.03524 0.02924 -0.0561 0.6347 1.0000
5.500 0.7362 0.03476 0.02881 -0.0569 0.6337 1.0000
5.750 0.7342 0.03601 0.03009 -0.0540 0.6226 1.0000
6.000 0.7678 0.03559 0.02976 -0.0546 0.6212 1.0000
6.250 0.8040 0.03499 0.02924 -0.0553 0.6202 1.0000
6.500 0.8409 0.03433 0.02869 -0.0561 0.6195 1.0000
6.750 0.8397 0.03572 0.03012 -0.0537 0.6077 1.0000
7.000 0.8663 0.03560 0.03013 -0.0536 0.6039 1.0000
7.250 0.9135 0.03414 0.02882 -0.0551 0.6059 1.0000
8.000 1.0686 0.02392 0.01910 -0.0574 0.5907 1.0000
8.250 1.0870 0.02270 0.01791 -0.0554 0.5587 1.0000
8.500 1.1124 0.02036 0.01452 -0.0516 0.4122 1.0000
8.750 1.0870 0.02335 0.01695 -0.0465 0.3327 1.0000
9.000 1.0627 0.02662 0.01969 -0.0421 0.2535 1.0000
9.250 1.0324 0.03051 0.02287 -0.0375 0.1516 1.0000
9.500 1.0103 0.03405 0.02576 -0.0339 0.0618 1.0000
9.750 1.0028 0.03677 0.02825 -0.0313 0.0347 1.0000
10.000 1.0078 0.03866 0.03024 -0.0298 0.0307 1.0000
10.250 1.0119 0.04068 0.03237 -0.0285 0.0256 1.0000
10.500 1.0119 0.04309 0.03486 -0.0269 0.0235 1.0000
10.750 1.0137 0.04537 0.03724 -0.0255 0.0222 1.0000
11.000 1.0191 0.04733 0.03929 -0.0242 0.0216 1.0000
11.250 1.0265 0.04910 0.04114 -0.0229 0.0212 1.0000
11.500 1.0354 0.05069 0.04279 -0.0213 0.0204 1.0000
11.750 1.0487 0.05188 0.04404 -0.0198 0.0196 1.0000
12.000 1.0679 0.05265 0.04485 -0.0180 0.0192 1.0000
12.250 1.0955 0.05313 0.04543 -0.0163 0.0193 1.0000
12.500 1.1247 0.05412 0.04661 -0.0151 0.0188 1.0000
12.750 1.1612 0.05578 0.04855 -0.0140 0.0198 1.0000
13.000 1.1657 0.05775 0.05046 -0.0135 0.0166 1.0000
13.250 1.1883 0.06112 0.05443 -0.0117 0.0190 1.0000
13.500 1.1981 0.06565 0.05935 -0.0100 0.0208 1.0000
13.750 1.0077 0.05787 0.05182 0.0066 0.0184 1.0000
14.000 1.0047 0.06177 0.05607 0.0083 0.0190 1.0000
14.250 0.9917 0.06540 0.06000 0.0100 0.0200 1.0000
14.500 0.9702 0.06903 0.06391 0.0115 0.0204 1.0000
14.750 0.9543 0.07281 0.06793 0.0121 0.0212 1.0000
15.000 0.9352 0.07714 0.07249 0.0123 0.0218 1.0000
15.250 0.9147 0.08193 0.07776 0.0125 0.0265 1.0000
15.500 0.8847 0.08748 0.08358 0.0111 0.0277 1.0000
15.750 0.8588 0.09282 0.08913 0.0092 0.0283 1.0000
16.000 0.8327 0.09853 0.09503 0.0065 0.0286 1.0000
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