FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 200,000 Max Cl/Cd: 54.49 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx68h120-il-200000.txt Download as CSV file: xf-fx68h120-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 68-H-120
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4835 0.08194 0.07890 -0.0358 1.0000 0.0334
-10.000 -0.5972 0.05330 0.04992 -0.0604 1.0000 0.0249
-9.750 -0.6194 0.05029 0.04675 -0.0594 1.0000 0.0248
-9.500 -0.6425 0.04998 0.04636 -0.0535 1.0000 0.0245
-9.250 -0.6683 0.04882 0.04510 -0.0475 1.0000 0.0245
-9.000 -0.6836 0.04731 0.04343 -0.0429 0.9996 0.0244
-8.750 -0.6715 0.04368 0.03941 -0.0443 0.9944 0.0242
-8.500 -0.6753 0.03741 0.03258 -0.0442 0.9882 0.0249
-8.250 -0.6591 0.03391 0.02863 -0.0445 0.9845 0.0251
-8.000 -0.6449 0.03099 0.02535 -0.0437 0.9802 0.0256
-7.750 -0.6247 0.02852 0.02250 -0.0433 0.9762 0.0258
-7.500 -0.5993 0.02630 0.01995 -0.0435 0.9733 0.0262
-7.250 -0.5717 0.02447 0.01790 -0.0440 0.9712 0.0274
-7.000 -0.5545 0.02323 0.01651 -0.0423 0.9666 0.0281
-6.750 -0.5287 0.02198 0.01510 -0.0421 0.9632 0.0296
-6.500 -0.4990 0.02096 0.01392 -0.0426 0.9607 0.0322
-6.250 -0.4705 0.01964 0.01252 -0.0431 0.9587 0.0361
-6.000 -0.4564 0.01897 0.01180 -0.0407 0.9535 0.0400
-5.750 -0.4333 0.01798 0.01075 -0.0398 0.9497 0.0496
-5.500 -0.4047 0.01708 0.01019 -0.0402 0.9472 0.1150
-5.250 -0.3665 0.01739 0.01039 -0.0424 0.9454 0.1423
-5.000 -0.3530 0.01761 0.01053 -0.0397 0.9395 0.1550
-4.750 -0.3247 0.01774 0.01060 -0.0401 0.9358 0.1706
-4.500 -0.2875 0.01767 0.01048 -0.0421 0.9331 0.1858
-4.250 -0.2564 0.01742 0.01016 -0.0426 0.9264 0.1964
-4.000 -0.2149 0.01701 0.00967 -0.0448 0.9200 0.2080
-3.750 -0.1852 0.01668 0.00935 -0.0448 0.9124 0.2174
-3.500 -0.1537 0.01627 0.00895 -0.0452 0.9065 0.2264
-3.250 -0.1266 0.01602 0.00867 -0.0447 0.9006 0.2366
-3.000 -0.1016 0.01575 0.00841 -0.0439 0.8940 0.2474
-2.750 -0.0725 0.01537 0.00809 -0.0436 0.8897 0.2607
-2.500 -0.0523 0.01515 0.00795 -0.0421 0.8814 0.2770
-2.250 -0.0264 0.01470 0.00765 -0.0411 0.8764 0.3024
-2.000 -0.0073 0.01432 0.00749 -0.0393 0.8679 0.3452
-1.750 0.0117 0.01355 0.00721 -0.0370 0.8622 0.4548
-1.500 0.0221 0.01275 0.00719 -0.0332 0.8531 0.6302
-1.250 0.1035 0.01191 0.00713 -0.0416 0.8502 0.8877
-1.000 0.1510 0.01190 0.00704 -0.0442 0.8424 0.9304
-0.750 0.1904 0.01181 0.00683 -0.0451 0.8344 0.9558
-0.500 0.2429 0.01167 0.00660 -0.0492 0.8239 0.9731
-0.250 0.2933 0.01140 0.00623 -0.0530 0.8133 0.9872
0.000 0.3463 0.01098 0.00571 -0.0576 0.8020 0.9999
0.250 0.3665 0.01073 0.00539 -0.0558 0.7887 1.0000
0.500 0.3873 0.01052 0.00512 -0.0542 0.7735 1.0000
0.750 0.4086 0.01032 0.00486 -0.0526 0.7553 1.0000
1.000 0.4299 0.01013 0.00456 -0.0509 0.7344 1.0000
1.250 0.4519 0.00999 0.00434 -0.0494 0.7055 1.0000
1.500 0.4735 0.00991 0.00409 -0.0479 0.6631 1.0000
1.750 0.4940 0.00999 0.00383 -0.0460 0.5973 1.0000
2.000 0.5142 0.01038 0.00377 -0.0445 0.5328 1.0000
2.250 0.5353 0.01083 0.00388 -0.0433 0.4857 1.0000
2.500 0.5570 0.01124 0.00404 -0.0423 0.4501 1.0000
2.750 0.5789 0.01162 0.00424 -0.0414 0.4207 1.0000
3.000 0.6008 0.01199 0.00444 -0.0404 0.3955 1.0000
3.250 0.6228 0.01233 0.00466 -0.0395 0.3728 1.0000
3.500 0.6445 0.01271 0.00489 -0.0385 0.3530 1.0000
3.750 0.6661 0.01308 0.00515 -0.0375 0.3347 1.0000
4.000 0.6878 0.01344 0.00542 -0.0365 0.3177 1.0000
4.250 0.7093 0.01381 0.00570 -0.0354 0.3027 1.0000
4.500 0.7307 0.01420 0.00600 -0.0344 0.2897 1.0000
4.750 0.7519 0.01462 0.00633 -0.0333 0.2788 1.0000
5.000 0.7737 0.01497 0.00667 -0.0322 0.2686 1.0000
5.250 0.7953 0.01538 0.00704 -0.0312 0.2599 1.0000
5.500 0.8167 0.01583 0.00741 -0.0301 0.2525 1.0000
5.750 0.8388 0.01622 0.00785 -0.0291 0.2455 1.0000
6.000 0.8605 0.01666 0.00824 -0.0282 0.2395 1.0000
6.250 0.8826 0.01712 0.00872 -0.0272 0.2340 1.0000
6.500 0.9041 0.01748 0.00910 -0.0262 0.2276 1.0000
6.750 0.9247 0.01787 0.00948 -0.0251 0.2204 1.0000
7.000 0.9439 0.01808 0.00969 -0.0237 0.2112 1.0000
7.250 0.9630 0.01828 0.00999 -0.0224 0.2017 1.0000
7.500 0.9820 0.01865 0.01032 -0.0211 0.1946 1.0000
7.750 1.0002 0.01875 0.01051 -0.0196 0.1840 1.0000
8.000 1.0188 0.01889 0.01073 -0.0182 0.1720 1.0000
8.250 1.0370 0.01903 0.01080 -0.0168 0.1484 1.0000
8.500 1.0547 0.01946 0.01112 -0.0153 0.1228 1.0000
9.000 1.0621 0.02264 0.01364 -0.0088 0.0246 1.0000
9.250 1.0721 0.02352 0.01464 -0.0061 0.0224 1.0000
9.500 1.0789 0.02457 0.01587 -0.0031 0.0201 1.0000
9.750 1.0876 0.02552 0.01698 -0.0005 0.0194 1.0000
10.000 1.0956 0.02658 0.01821 0.0019 0.0186 1.0000
10.250 1.1022 0.02776 0.01956 0.0043 0.0179 1.0000
10.500 1.1067 0.02913 0.02111 0.0066 0.0174 1.0000
10.750 1.1092 0.03066 0.02281 0.0089 0.0172 1.0000
11.000 1.1092 0.03243 0.02475 0.0111 0.0170 1.0000
11.250 1.1077 0.03441 0.02687 0.0130 0.0168 1.0000
11.500 1.1049 0.03661 0.02921 0.0146 0.0167 1.0000
11.750 1.1005 0.03911 0.03184 0.0158 0.0168 1.0000
12.000 1.0929 0.04212 0.03498 0.0167 0.0166 1.0000
12.250 1.0872 0.04520 0.03817 0.0171 0.0166 1.0000
12.500 1.0802 0.04865 0.04177 0.0170 0.0166 1.0000
12.750 1.0738 0.05227 0.04549 0.0167 0.0165 1.0000
13.000 1.0691 0.05585 0.04916 0.0162 0.0166 1.0000
13.250 1.0669 0.05922 0.05263 0.0156 0.0168 1.0000
13.500 1.0659 0.06247 0.05595 0.0153 0.0170 1.0000
13.750 1.0662 0.06550 0.05905 0.0153 0.0170 1.0000
14.000 1.0688 0.06827 0.06189 0.0153 0.0172 1.0000
14.250 1.0744 0.07055 0.06422 0.0159 0.0175 1.0000
14.500 1.0831 0.07241 0.06614 0.0171 0.0179 1.0000
14.750 1.0890 0.07486 0.06867 0.0176 0.0183 1.0000
15.000 1.0965 0.07724 0.07114 0.0186 0.0188 1.0000
15.250 1.1248 0.07765 0.07156 0.0226 0.0200 1.0000
15.500 1.1224 0.08106 0.07510 0.0210 0.0203 1.0000
15.750 1.1172 0.08512 0.07934 0.0189 0.0207 1.0000
16.000 1.1093 0.08994 0.08438 0.0162 0.0213 1.0000
16.250 1.0987 0.09573 0.09048 0.0132 0.0225 1.0000
16.500 1.0841 0.10229 0.09729 0.0097 0.0233 1.0000
16.750 1.0694 0.10912 0.10436 0.0062 0.0244 1.0000
17.000 1.0556 0.11587 0.11129 0.0025 0.0249 1.0000
17.250 1.0392 0.12336 0.11895 -0.0017 0.0255 1.0000
17.500 1.0235 0.13091 0.12665 -0.0062 0.0258 1.0000
17.750 1.0049 0.13940 0.13529 -0.0114 0.0261 1.0000
18.000 0.9850 0.14860 0.14464 -0.0172 0.0263 1.0000
18.250 0.9623 0.15908 0.15524 -0.0237 0.0265 1.0000
18.500 0.9378 0.17072 0.16699 -0.0309 0.0266 1.0000
18.750 0.7331 0.15966 0.15644 -0.0260 0.0232 1.0000
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