FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.39 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx68h120-il-1000000.txt Download as CSV file: xf-fx68h120-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7999 0.05832 0.05620 -0.0396 1.0000 0.0049
-12.500 -0.8031 0.05201 0.04979 -0.0453 1.0000 0.0048
-12.250 -0.8094 0.04382 0.04135 -0.0556 0.9522 0.0048
-12.000 -0.8432 0.03855 0.03580 -0.0569 0.9297 0.0049
-11.750 -0.8560 0.03622 0.03330 -0.0550 0.9187 0.0048
-11.500 -0.8729 0.03379 0.03068 -0.0515 0.9092 0.0048
-11.250 -0.8843 0.03186 0.02855 -0.0473 0.9021 0.0049
-11.000 -0.8927 0.02900 0.02542 -0.0440 0.8961 0.0049
-10.750 -0.8926 0.02662 0.02279 -0.0412 0.8914 0.0051
-10.500 -0.8822 0.02502 0.02102 -0.0394 0.8875 0.0052
-10.250 -0.8678 0.02370 0.01958 -0.0379 0.8837 0.0053
-10.000 -0.8503 0.02270 0.01847 -0.0367 0.8803 0.0055
-9.750 -0.8301 0.02203 0.01772 -0.0358 0.8775 0.0058
-9.500 -0.8098 0.02126 0.01682 -0.0349 0.8746 0.0060
-9.250 -0.7892 0.02037 0.01584 -0.0340 0.8717 0.0063
-9.000 -0.7677 0.01958 0.01494 -0.0332 0.8686 0.0066
-8.750 -0.7470 0.01863 0.01386 -0.0321 0.8657 0.0068
-8.500 -0.7239 0.01804 0.01317 -0.0313 0.8632 0.0071
-8.250 -0.7016 0.01726 0.01227 -0.0305 0.8606 0.0072
-8.000 -0.6775 0.01664 0.01156 -0.0299 0.8581 0.0073
-7.750 -0.6577 0.01538 0.01015 -0.0286 0.8552 0.0076
-7.500 -0.6375 0.01421 0.00882 -0.0273 0.8524 0.0079
-7.250 -0.6148 0.01340 0.00789 -0.0264 0.8499 0.0084
-7.000 -0.5902 0.01289 0.00729 -0.0258 0.8476 0.0088
-6.750 -0.5641 0.01247 0.00683 -0.0254 0.8454 0.0093
-6.500 -0.5379 0.01206 0.00639 -0.0251 0.8428 0.0100
-6.250 -0.5117 0.01168 0.00596 -0.0247 0.8403 0.0107
-6.000 -0.4852 0.01134 0.00555 -0.0243 0.8379 0.0111
-5.750 -0.4598 0.01084 0.00494 -0.0237 0.8351 0.0121
-5.500 -0.4338 0.01043 0.00446 -0.0232 0.8307 0.0137
-5.250 -0.4073 0.01008 0.00408 -0.0227 0.8249 0.0159
-5.000 -0.3829 0.00949 0.00356 -0.0219 0.8201 0.0364
-4.750 -0.3584 0.00887 0.00318 -0.0213 0.8160 0.0800
-4.500 -0.3317 0.00859 0.00301 -0.0211 0.8116 0.1043
-4.250 -0.3043 0.00843 0.00286 -0.0208 0.8075 0.1160
-4.000 -0.2765 0.00832 0.00272 -0.0207 0.8034 0.1234
-3.750 -0.2485 0.00818 0.00260 -0.0206 0.7986 0.1317
-3.500 -0.2206 0.00807 0.00247 -0.0205 0.7942 0.1389
-3.250 -0.1928 0.00797 0.00237 -0.0203 0.7899 0.1472
-3.000 -0.1647 0.00784 0.00227 -0.0203 0.7851 0.1552
-2.750 -0.1366 0.00774 0.00216 -0.0202 0.7801 0.1624
-2.500 -0.1089 0.00761 0.00202 -0.0200 0.7745 0.1688
-2.250 -0.0809 0.00749 0.00190 -0.0199 0.7665 0.1752
-2.000 -0.0531 0.00737 0.00178 -0.0197 0.7589 0.1835
-1.500 0.0025 0.00715 0.00158 -0.0195 0.7415 0.2060
-1.250 0.0299 0.00701 0.00149 -0.0193 0.7314 0.2266
-1.000 0.0569 0.00685 0.00140 -0.0191 0.7186 0.2591
-0.750 0.0834 0.00666 0.00133 -0.0188 0.7024 0.3057
-0.500 0.1093 0.00645 0.00126 -0.0184 0.6813 0.3664
-0.250 0.1340 0.00627 0.00121 -0.0178 0.6478 0.4411
0.000 0.1566 0.00624 0.00120 -0.0168 0.5836 0.5260
0.250 0.1769 0.00622 0.00126 -0.0155 0.5210 0.6275
0.500 0.1944 0.00601 0.00132 -0.0134 0.4820 0.7543
0.750 0.2163 0.00579 0.00144 -0.0119 0.4511 0.8877
1.000 0.2622 0.00602 0.00162 -0.0157 0.4183 0.9393
1.250 0.2979 0.00626 0.00174 -0.0174 0.3925 0.9560
1.500 0.3384 0.00650 0.00185 -0.0201 0.3681 0.9633
1.750 0.3707 0.00674 0.00198 -0.0210 0.3480 0.9713
2.000 0.4101 0.00698 0.00210 -0.0236 0.3263 0.9748
2.500 0.4749 0.00741 0.00234 -0.0256 0.2935 0.9833
2.750 0.5141 0.00759 0.00244 -0.0282 0.2778 0.9851
3.000 0.5558 0.00780 0.00256 -0.0312 0.2623 0.9880
3.250 0.6051 0.00807 0.00273 -0.0359 0.2463 0.9941
3.500 0.6612 0.00824 0.00281 -0.0421 0.2306 0.9986
3.750 0.6960 0.00840 0.00290 -0.0438 0.2193 1.0000
4.000 0.7202 0.00857 0.00301 -0.0432 0.2094 1.0000
4.250 0.7446 0.00871 0.00311 -0.0426 0.2019 1.0000
4.500 0.7686 0.00888 0.00325 -0.0420 0.1940 1.0000
4.750 0.7927 0.00904 0.00338 -0.0413 0.1873 1.0000
5.000 0.8164 0.00922 0.00352 -0.0407 0.1787 1.0000
5.250 0.8401 0.00941 0.00366 -0.0400 0.1720 1.0000
5.500 0.8637 0.00959 0.00384 -0.0392 0.1667 1.0000
5.750 0.8873 0.00976 0.00399 -0.0385 0.1609 1.0000
6.000 0.9103 0.00999 0.00417 -0.0377 0.1529 1.0000
6.250 0.9331 0.01021 0.00434 -0.0369 0.1440 1.0000
6.500 0.9553 0.01048 0.00454 -0.0360 0.1317 1.0000
6.750 0.9634 0.01207 0.00553 -0.0332 0.0420 1.0000
7.000 0.9792 0.01289 0.00628 -0.0312 0.0099 1.0000
7.250 0.9996 0.01325 0.00669 -0.0299 0.0082 1.0000
7.500 1.0197 0.01362 0.00709 -0.0286 0.0074 1.0000
7.750 1.0387 0.01405 0.00758 -0.0271 0.0068 1.0000
8.000 1.0568 0.01455 0.00812 -0.0255 0.0062 1.0000
8.250 1.0718 0.01529 0.00897 -0.0233 0.0057 1.0000
8.500 1.0882 0.01587 0.00963 -0.0214 0.0053 1.0000
8.750 1.1046 0.01641 0.01024 -0.0196 0.0051 1.0000
9.000 1.1192 0.01706 0.01095 -0.0175 0.0050 1.0000
9.250 1.1322 0.01775 0.01172 -0.0152 0.0048 1.0000
9.500 1.1431 0.01855 0.01260 -0.0126 0.0046 1.0000
9.750 1.1496 0.01935 0.01348 -0.0092 0.0046 1.0000
10.000 1.1519 0.02023 0.01444 -0.0054 0.0046 1.0000
10.250 1.1556 0.02124 0.01554 -0.0022 0.0047 1.0000
10.500 1.1590 0.02243 0.01682 0.0006 0.0046 1.0000
10.750 1.1645 0.02360 0.01806 0.0029 0.0045 1.0000
11.000 1.1639 0.02526 0.01982 0.0056 0.0046 1.0000
11.250 1.1640 0.02700 0.02165 0.0079 0.0046 1.0000
11.500 1.1685 0.02852 0.02327 0.0095 0.0045 1.0000
11.750 1.1757 0.02991 0.02471 0.0106 0.0043 1.0000
12.000 1.1666 0.03277 0.02768 0.0126 0.0045 1.0000
12.250 1.1701 0.03468 0.02967 0.0135 0.0043 1.0000
12.500 1.1694 0.03710 0.03217 0.0143 0.0043 1.0000
12.750 1.1598 0.04053 0.03571 0.0153 0.0045 1.0000
13.000 1.1623 0.04294 0.03819 0.0153 0.0043 1.0000
13.250 1.1590 0.04605 0.04140 0.0154 0.0044 1.0000
13.500 1.1578 0.04909 0.04452 0.0152 0.0044 1.0000
13.750 1.1522 0.05246 0.04796 0.0163 0.0048 1.0000
14.000 1.1521 0.05539 0.05096 0.0164 0.0049 1.0000
14.250 1.1519 0.05869 0.05436 0.0154 0.0048 1.0000
14.500 1.1673 0.05957 0.05531 0.0188 0.0065 1.0000
14.750 1.1661 0.06290 0.05876 0.0183 0.0065 1.0000
15.000 1.1777 0.06419 0.05991 0.0196 0.0059 1.0000
15.250 1.1752 0.06782 0.06367 0.0185 0.0060 1.0000
15.500 1.1723 0.07158 0.06755 0.0174 0.0060 1.0000
15.750 1.1699 0.07526 0.07132 0.0165 0.0060 1.0000
16.000 1.1704 0.07849 0.07460 0.0165 0.0059 1.0000
16.250 1.1514 0.08614 0.08250 0.0184 0.0055 1.0000
16.500 1.1360 0.09177 0.08828 0.0154 0.0055 1.0000
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