FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 50,000 Max Cl/Cd: 28.34 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx68h120-il-50000.txt Download as CSV file: xf-fx68h120-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3899 0.11462 0.10826 -0.0151 1.0000 0.2240
-9.750 -0.3852 0.11137 0.10503 -0.0159 1.0000 0.2320
-9.500 -0.3909 0.10815 0.10191 -0.0175 1.0000 0.2369
-9.250 -0.3818 0.10448 0.09826 -0.0175 1.0000 0.2468
-9.000 -0.3743 0.10076 0.09458 -0.0174 1.0000 0.2582
-8.750 -0.3718 0.09754 0.09143 -0.0174 1.0000 0.2726
-8.500 -0.3699 0.09429 0.08823 -0.0172 1.0000 0.2857
-8.250 -0.3941 0.09287 0.08698 -0.0185 1.0000 0.2924
-8.000 -0.5222 0.07409 0.06838 -0.0379 1.0000 0.1208
-7.750 -0.5302 0.07100 0.06530 -0.0354 1.0000 0.1199
-7.500 -0.5426 0.06772 0.06201 -0.0329 1.0000 0.1189
-7.250 -0.5560 0.06412 0.05833 -0.0305 1.0000 0.1176
-7.000 -0.5682 0.06027 0.05434 -0.0281 1.0000 0.1163
-6.750 -0.5785 0.05610 0.04993 -0.0257 1.0000 0.1151
-6.500 -0.5851 0.05191 0.04541 -0.0232 1.0000 0.1148
-6.250 -0.5874 0.04786 0.04094 -0.0206 1.0000 0.1161
-6.000 -0.5873 0.04384 0.03629 -0.0179 1.0000 0.1195
-5.750 -0.5762 0.04216 0.03457 -0.0156 1.0000 0.1303
-5.500 -0.5663 0.03965 0.03178 -0.0131 1.0000 0.1415
-5.250 -0.5552 0.03755 0.02930 -0.0106 1.0000 0.1599
-5.000 -0.5422 0.03571 0.02735 -0.0082 1.0000 0.1839
-4.750 -0.5290 0.03436 0.02591 -0.0057 1.0000 0.2152
-4.500 -0.5147 0.03311 0.02453 -0.0034 1.0000 0.2461
-4.250 -0.4985 0.03198 0.02333 -0.0015 1.0000 0.2724
-4.000 -0.4810 0.03078 0.02188 0.0002 1.0000 0.2948
-3.750 -0.4617 0.02974 0.02075 0.0016 1.0000 0.3135
-3.500 -0.4419 0.02879 0.01962 0.0028 1.0000 0.3312
-3.250 -0.4209 0.02788 0.01852 0.0038 1.0000 0.3471
-3.000 -0.3997 0.02710 0.01752 0.0048 1.0000 0.3641
-2.750 -0.3772 0.02637 0.01667 0.0054 1.0000 0.3802
-2.500 -0.3541 0.02571 0.01602 0.0060 1.0000 0.3993
-2.250 -0.3301 0.02517 0.01539 0.0064 1.0000 0.4221
-2.000 -0.3042 0.02464 0.01491 0.0064 1.0000 0.4501
-1.750 -0.2797 0.02407 0.01452 0.0067 1.0000 0.4921
-1.500 -0.1403 0.02263 0.01470 -0.0121 1.0000 1.0000
-1.250 -0.1271 0.02283 0.01453 -0.0106 1.0000 1.0000
-1.000 -0.1141 0.02310 0.01450 -0.0091 1.0000 1.0000
-0.750 -0.1012 0.02344 0.01461 -0.0076 1.0000 1.0000
-0.500 -0.0884 0.02385 0.01482 -0.0062 1.0000 1.0000
-0.250 -0.0760 0.02434 0.01514 -0.0049 1.0000 1.0000
0.000 -0.0336 0.02545 0.01606 -0.0095 0.9888 1.0000
0.250 0.0430 0.02709 0.01748 -0.0201 0.9617 1.0000
0.500 0.1149 0.02837 0.01860 -0.0291 0.9333 1.0000
0.750 0.1855 0.02925 0.01941 -0.0372 0.9041 1.0000
1.000 0.2505 0.02969 0.01979 -0.0435 0.8743 1.0000
1.250 0.3120 0.02971 0.01982 -0.0487 0.8436 1.0000
1.500 0.3738 0.02924 0.01938 -0.0530 0.8135 1.0000
1.750 0.4235 0.02841 0.01857 -0.0545 0.7838 1.0000
2.000 0.4653 0.02738 0.01756 -0.0543 0.7546 1.0000
2.250 0.5013 0.02625 0.01640 -0.0529 0.7253 1.0000
2.500 0.5340 0.02508 0.01518 -0.0508 0.6956 1.0000
2.750 0.5648 0.02396 0.01399 -0.0485 0.6652 1.0000
3.000 0.5897 0.02336 0.01323 -0.0458 0.6304 1.0000
3.250 0.6159 0.02296 0.01258 -0.0435 0.5970 1.0000
3.500 0.6406 0.02302 0.01234 -0.0414 0.5644 1.0000
3.750 0.6632 0.02353 0.01265 -0.0397 0.5335 1.0000
4.000 0.6864 0.02422 0.01310 -0.0382 0.5066 1.0000
4.250 0.7088 0.02506 0.01379 -0.0369 0.4826 1.0000
4.500 0.7311 0.02603 0.01465 -0.0358 0.4625 1.0000
4.750 0.7526 0.02705 0.01565 -0.0347 0.4445 1.0000
5.000 0.7744 0.02809 0.01669 -0.0336 0.4285 1.0000
5.250 0.7957 0.02919 0.01779 -0.0326 0.4145 1.0000
5.500 0.8169 0.03040 0.01905 -0.0317 0.4029 1.0000
5.750 0.8402 0.03159 0.02020 -0.0309 0.3933 1.0000
6.000 0.8577 0.03306 0.02192 -0.0298 0.3837 1.0000
6.250 0.8757 0.03457 0.02357 -0.0286 0.3752 1.0000
6.500 0.8968 0.03586 0.02491 -0.0277 0.3671 1.0000
6.750 0.9088 0.03783 0.02715 -0.0263 0.3603 1.0000
7.000 0.9245 0.03966 0.02916 -0.0251 0.3548 1.0000
7.250 0.9443 0.04144 0.03103 -0.0243 0.3504 1.0000
7.500 0.9426 0.04456 0.03455 -0.0223 0.3467 1.0000
7.750 0.9434 0.04756 0.03783 -0.0205 0.3430 1.0000
8.000 0.9541 0.04991 0.04038 -0.0192 0.3392 1.0000
8.250 0.9596 0.05277 0.04339 -0.0178 0.3359 1.0000
8.500 0.9237 0.05857 0.04942 -0.0151 0.3348 1.0000
8.750 0.8712 0.06609 0.05694 -0.0131 0.3356 1.0000
10.750 1.1505 0.05169 0.04317 -0.0012 0.2226 1.0000
11.000 1.1285 0.05509 0.04694 0.0023 0.2199 1.0000
11.250 1.0852 0.06198 0.05409 0.0052 0.2256 1.0000
11.500 1.0623 0.06630 0.05853 0.0069 0.2246 1.0000
11.750 1.0394 0.07130 0.06363 0.0074 0.2235 1.0000
12.000 1.1395 0.05302 0.04536 0.0138 0.1760 1.0000
12.250 1.1343 0.05382 0.04624 0.0158 0.1655 1.0000
12.500 1.1144 0.05740 0.05007 0.0165 0.1588 1.0000
12.750 1.0984 0.06083 0.05363 0.0166 0.1506 1.0000
13.000 1.0721 0.06688 0.05992 0.0150 0.1468 1.0000
13.250 1.0588 0.07122 0.06436 0.0135 0.1391 1.0000
13.500 1.0296 0.07937 0.07268 0.0100 0.1393 1.0000
13.750 0.9967 0.08901 0.08234 0.0056 0.1402 1.0000
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Polar data table (+)
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