FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.25 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx68h120-il-1000000-n5.txt Download as CSV file: xf-fx68h120-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8511 0.08489 0.08269 -0.0217 1.0000 0.0031
-14.500 -0.8939 0.07414 0.07182 -0.0282 1.0000 0.0028
-14.250 -0.9437 0.06184 0.05939 -0.0362 0.9712 0.0028
-14.000 -0.9900 0.04621 0.04343 -0.0488 0.9341 0.0028
-13.750 -1.0261 0.03799 0.03489 -0.0545 0.9128 0.0027
-13.500 -1.0270 0.03603 0.03282 -0.0540 0.9033 0.0027
-13.250 -1.0548 0.03264 0.02920 -0.0511 0.8919 0.0027
-13.000 -1.0717 0.03036 0.02672 -0.0469 0.8837 0.0028
-12.750 -1.0774 0.02859 0.02477 -0.0433 0.8777 0.0029
-12.500 -1.0699 0.02722 0.02325 -0.0413 0.8736 0.0029
-12.250 -1.0589 0.02596 0.02187 -0.0396 0.8696 0.0030
-12.000 -1.0438 0.02498 0.02080 -0.0383 0.8659 0.0031
-11.750 -1.0274 0.02408 0.01979 -0.0370 0.8625 0.0032
-11.500 -1.0099 0.02318 0.01879 -0.0359 0.8595 0.0033
-11.250 -0.9914 0.02231 0.01781 -0.0349 0.8564 0.0034
-11.000 -0.9709 0.02163 0.01705 -0.0340 0.8535 0.0035
-10.750 -0.9504 0.02092 0.01625 -0.0331 0.8508 0.0036
-10.500 -0.9303 0.02014 0.01536 -0.0322 0.8481 0.0037
-10.250 -0.9091 0.01940 0.01453 -0.0313 0.8455 0.0039
-10.000 -0.8874 0.01867 0.01371 -0.0305 0.8426 0.0040
-9.750 -0.8647 0.01806 0.01301 -0.0298 0.8399 0.0042
-9.500 -0.8428 0.01732 0.01216 -0.0290 0.8374 0.0043
-9.250 -0.8195 0.01676 0.01149 -0.0283 0.8351 0.0044
-9.000 -0.7959 0.01619 0.01083 -0.0277 0.8329 0.0045
-8.750 -0.7718 0.01563 0.01019 -0.0271 0.8304 0.0046
-8.500 -0.7469 0.01517 0.00967 -0.0266 0.8277 0.0046
-8.250 -0.7223 0.01466 0.00908 -0.0261 0.8252 0.0047
-8.000 -0.6997 0.01382 0.00812 -0.0252 0.8228 0.0050
-7.750 -0.6750 0.01329 0.00750 -0.0247 0.8207 0.0053
-7.500 -0.6497 0.01282 0.00697 -0.0242 0.8186 0.0055
-7.250 -0.6235 0.01245 0.00655 -0.0239 0.8162 0.0060
-7.000 -0.5972 0.01210 0.00616 -0.0236 0.8136 0.0063
-6.750 -0.5707 0.01177 0.00579 -0.0233 0.8112 0.0066
-6.500 -0.5441 0.01145 0.00543 -0.0230 0.8090 0.0070
-6.250 -0.5175 0.01116 0.00508 -0.0227 0.8069 0.0072
-6.000 -0.4907 0.01088 0.00474 -0.0224 0.8047 0.0075
-5.750 -0.4638 0.01054 0.00437 -0.0221 0.8016 0.0084
-5.500 -0.4369 0.01025 0.00404 -0.0218 0.7962 0.0093
-5.250 -0.4101 0.01000 0.00375 -0.0215 0.7895 0.0106
-5.000 -0.3831 0.00972 0.00347 -0.0212 0.7822 0.0139
-4.500 -0.3302 0.00904 0.00288 -0.0206 0.7714 0.0396
-4.250 -0.3041 0.00868 0.00261 -0.0202 0.7657 0.0632
-4.000 -0.2773 0.00841 0.00241 -0.0200 0.7596 0.0845
-3.750 -0.2500 0.00822 0.00227 -0.0198 0.7521 0.1002
-3.500 -0.2224 0.00808 0.00215 -0.0197 0.7450 0.1125
-3.250 -0.1946 0.00797 0.00204 -0.0195 0.7372 0.1234
-3.000 -0.1667 0.00786 0.00194 -0.0195 0.7296 0.1332
-2.750 -0.1389 0.00776 0.00184 -0.0193 0.7203 0.1414
-2.500 -0.1109 0.00770 0.00173 -0.0192 0.7072 0.1461
-2.250 -0.0830 0.00768 0.00163 -0.0191 0.6838 0.1496
-2.000 -0.0559 0.00770 0.00154 -0.0189 0.6458 0.1559
-1.750 -0.0296 0.00791 0.00149 -0.0187 0.5773 0.1608
-1.500 -0.0032 0.00814 0.00150 -0.0185 0.5178 0.1657
-1.250 0.0234 0.00828 0.00150 -0.0183 0.4766 0.1729
-1.000 0.0503 0.00838 0.00149 -0.0181 0.4436 0.1815
-0.750 0.0772 0.00846 0.00149 -0.0180 0.4155 0.1918
-0.500 0.1041 0.00850 0.00148 -0.0178 0.3946 0.2045
-0.250 0.1310 0.00853 0.00148 -0.0176 0.3757 0.2205
0.000 0.1577 0.00854 0.00149 -0.0174 0.3561 0.2416
0.250 0.1839 0.00856 0.00150 -0.0172 0.3367 0.2708
0.500 0.2099 0.00851 0.00152 -0.0169 0.3212 0.3108
0.750 0.2357 0.00845 0.00155 -0.0165 0.3078 0.3572
1.000 0.2614 0.00839 0.00158 -0.0161 0.2954 0.4069
1.250 0.2867 0.00831 0.00161 -0.0157 0.2837 0.4615
1.500 0.3116 0.00822 0.00166 -0.0152 0.2728 0.5218
1.750 0.3352 0.00809 0.00171 -0.0144 0.2620 0.5981
2.000 0.3564 0.00789 0.00176 -0.0131 0.2504 0.6949
2.250 0.3761 0.00769 0.00183 -0.0113 0.2397 0.7885
2.500 0.3989 0.00754 0.00194 -0.0101 0.2296 0.8777
2.750 0.4422 0.00765 0.00212 -0.0134 0.2191 0.9317
3.000 0.4864 0.00786 0.00227 -0.0171 0.2085 0.9516
3.250 0.5290 0.00806 0.00243 -0.0203 0.1995 0.9646
3.500 0.5709 0.00831 0.00263 -0.0233 0.1919 0.9778
3.750 0.6140 0.00856 0.00283 -0.0267 0.1842 0.9857
4.000 0.6572 0.00875 0.00299 -0.0301 0.1784 0.9897
4.250 0.6926 0.00893 0.00313 -0.0318 0.1729 0.9926
4.500 0.7235 0.00911 0.00327 -0.0326 0.1673 0.9943
4.750 0.7559 0.00924 0.00340 -0.0337 0.1636 0.9953
5.000 0.7867 0.00946 0.00355 -0.0346 0.1540 0.9964
5.250 0.8175 0.00962 0.00368 -0.0354 0.1480 0.9974
5.500 0.8478 0.00983 0.00385 -0.0361 0.1414 0.9985
5.750 0.8782 0.01000 0.00401 -0.0369 0.1359 0.9993
6.000 0.9072 0.01028 0.00421 -0.0374 0.1243 1.0000
6.250 0.9286 0.01064 0.00446 -0.0364 0.1076 1.0000
6.500 0.9364 0.01231 0.00563 -0.0335 0.0128 1.0000
6.750 0.9575 0.01264 0.00595 -0.0324 0.0079 1.0000
7.000 0.9784 0.01295 0.00629 -0.0312 0.0066 1.0000
7.250 0.9991 0.01327 0.00664 -0.0300 0.0054 1.0000
7.500 1.0198 0.01357 0.00695 -0.0288 0.0049 1.0000
7.750 1.0399 0.01390 0.00731 -0.0275 0.0044 1.0000
8.000 1.0595 0.01425 0.00769 -0.0262 0.0041 1.0000
8.250 1.0784 0.01466 0.00812 -0.0247 0.0037 1.0000
8.500 1.0957 0.01518 0.00869 -0.0230 0.0033 1.0000
8.750 1.1142 0.01556 0.00912 -0.0215 0.0032 1.0000
9.000 1.1317 0.01601 0.00962 -0.0199 0.0031 1.0000
9.250 1.1489 0.01646 0.01010 -0.0182 0.0029 1.0000
9.500 1.1653 0.01694 0.01062 -0.0164 0.0026 1.0000
9.750 1.1804 0.01748 0.01122 -0.0145 0.0026 1.0000
10.000 1.1946 0.01808 0.01188 -0.0125 0.0025 1.0000
10.250 1.2050 0.01866 0.01251 -0.0098 0.0024 1.0000
10.500 1.2147 0.01924 0.01314 -0.0071 0.0023 1.0000
10.750 1.2243 0.01996 0.01394 -0.0046 0.0022 1.0000
11.000 1.2341 0.02076 0.01481 -0.0024 0.0022 1.0000
11.250 1.2444 0.02160 0.01570 -0.0004 0.0021 1.0000
11.500 1.2537 0.02255 0.01673 0.0015 0.0021 1.0000
11.750 1.2621 0.02361 0.01787 0.0034 0.0021 1.0000
12.000 1.2686 0.02485 0.01919 0.0052 0.0020 1.0000
12.250 1.2742 0.02621 0.02063 0.0069 0.0019 1.0000
12.500 1.2769 0.02785 0.02236 0.0086 0.0019 1.0000
12.750 1.2732 0.03009 0.02474 0.0104 0.0018 1.0000
13.000 1.2692 0.03252 0.02728 0.0118 0.0018 1.0000
13.250 1.2715 0.03454 0.02938 0.0126 0.0018 1.0000
13.500 1.2648 0.03756 0.03253 0.0133 0.0017 1.0000
13.750 1.2474 0.04207 0.03720 0.0133 0.0017 1.0000
14.000 1.2350 0.04651 0.04178 0.0125 0.0017 1.0000
14.250 1.2326 0.05008 0.04544 0.0114 0.0017 1.0000
14.500 1.2153 0.05619 0.05171 0.0090 0.0017 1.0000
14.750 1.2001 0.06233 0.05799 0.0063 0.0017 1.0000
15.000 1.2068 0.06518 0.06091 0.0051 0.0017 1.0000
15.250 1.1834 0.07278 0.06866 0.0018 0.0017 1.0000
15.500 1.1600 0.08021 0.07622 -0.0012 0.0017 1.0000
15.750 1.1405 0.08702 0.08314 -0.0039 0.0017 1.0000
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