FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 100,000 Max Cl/Cd: 40.97 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx68h120-il-100000-n5.txt Download as CSV file: xf-fx68h120-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5009 0.08700 0.08252 -0.0307 1.0000 0.0215
-10.500 -0.5285 0.07630 0.07191 -0.0373 1.0000 0.0208
-10.250 -0.5760 0.06010 0.05559 -0.0518 1.0000 0.0198
-10.000 -0.6069 0.05278 0.04804 -0.0580 1.0000 0.0193
-9.750 -0.6290 0.04911 0.04418 -0.0573 1.0000 0.0192
-9.500 -0.6490 0.04659 0.04148 -0.0540 1.0000 0.0192
-9.250 -0.6692 0.04480 0.03951 -0.0491 1.0000 0.0192
-9.000 -0.6769 0.04222 0.03664 -0.0463 0.9960 0.0193
-8.750 -0.6664 0.03894 0.03294 -0.0466 0.9885 0.0198
-8.500 -0.6494 0.03598 0.02956 -0.0472 0.9832 0.0204
-8.250 -0.6317 0.03368 0.02689 -0.0470 0.9775 0.0213
-8.000 -0.6084 0.03173 0.02455 -0.0475 0.9733 0.0231
-7.750 -0.5864 0.02988 0.02235 -0.0475 0.9693 0.0245
-7.500 -0.5677 0.02814 0.02047 -0.0469 0.9645 0.0261
-7.250 -0.5438 0.02669 0.01883 -0.0469 0.9606 0.0279
-7.000 -0.5198 0.02544 0.01737 -0.0467 0.9568 0.0301
-6.750 -0.4999 0.02441 0.01610 -0.0455 0.9519 0.0327
-6.500 -0.4771 0.02322 0.01482 -0.0451 0.9480 0.0378
-6.250 -0.4508 0.02210 0.01365 -0.0453 0.9449 0.0491
-6.000 -0.4328 0.02121 0.01284 -0.0438 0.9396 0.0692
-5.750 -0.4073 0.02084 0.01255 -0.0437 0.9359 0.1056
-5.500 -0.3776 0.02088 0.01246 -0.0442 0.9328 0.1326
-5.250 -0.3531 0.02091 0.01236 -0.0438 0.9287 0.1513
-5.000 -0.3307 0.02085 0.01218 -0.0429 0.9241 0.1655
-4.750 -0.3032 0.02066 0.01183 -0.0429 0.9206 0.1777
-4.500 -0.2735 0.02034 0.01150 -0.0434 0.9178 0.1877
-4.250 -0.2528 0.02011 0.01117 -0.0422 0.9127 0.1954
-4.000 -0.2268 0.01986 0.01085 -0.0418 0.9084 0.2045
-3.750 -0.1975 0.01956 0.01054 -0.0421 0.9050 0.2135
-3.500 -0.1733 0.01931 0.01024 -0.0413 0.8980 0.2224
-3.250 -0.1414 0.01895 0.00984 -0.0417 0.8910 0.2344
-3.000 -0.1171 0.01860 0.00950 -0.0406 0.8809 0.2462
-2.750 -0.0885 0.01823 0.00914 -0.0403 0.8735 0.2609
-2.500 -0.0644 0.01792 0.00888 -0.0393 0.8650 0.2801
-2.250 -0.0397 0.01758 0.00864 -0.0384 0.8574 0.3077
-2.000 -0.0147 0.01717 0.00839 -0.0375 0.8500 0.3497
-1.750 0.0081 0.01675 0.00823 -0.0363 0.8418 0.4137
-1.500 0.0332 0.01612 0.00802 -0.0353 0.8348 0.5196
-1.250 0.0578 0.01548 0.00797 -0.0340 0.8258 0.6634
-1.000 0.1363 0.01493 0.00789 -0.0420 0.8204 0.8481
-0.750 0.1863 0.01486 0.00778 -0.0455 0.8100 0.9066
-0.500 0.2219 0.01482 0.00764 -0.0462 0.7989 0.9398
-0.250 0.2622 0.01470 0.00742 -0.0480 0.7862 0.9638
0.000 0.3049 0.01452 0.00714 -0.0505 0.7704 0.9831
0.250 0.3568 0.01419 0.00671 -0.0550 0.7510 1.0000
0.500 0.3772 0.01407 0.00651 -0.0533 0.7295 1.0000
0.750 0.3977 0.01393 0.00628 -0.0516 0.7045 1.0000
1.000 0.4184 0.01383 0.00605 -0.0498 0.6713 1.0000
1.250 0.4389 0.01372 0.00572 -0.0479 0.6275 1.0000
1.500 0.4589 0.01373 0.00538 -0.0458 0.5752 1.0000
1.750 0.4787 0.01397 0.00525 -0.0439 0.5268 1.0000
2.000 0.4988 0.01431 0.00529 -0.0424 0.4877 1.0000
2.250 0.5195 0.01467 0.00541 -0.0411 0.4557 1.0000
2.500 0.5403 0.01502 0.00557 -0.0399 0.4280 1.0000
2.750 0.5614 0.01537 0.00577 -0.0387 0.4044 1.0000
3.000 0.5826 0.01571 0.00597 -0.0376 0.3832 1.0000
3.250 0.6038 0.01607 0.00619 -0.0365 0.3647 1.0000
3.500 0.6251 0.01641 0.00643 -0.0354 0.3473 1.0000
3.750 0.6463 0.01676 0.00671 -0.0343 0.3313 1.0000
4.000 0.6675 0.01713 0.00699 -0.0332 0.3165 1.0000
4.250 0.6886 0.01751 0.00729 -0.0320 0.3033 1.0000
4.500 0.7095 0.01790 0.00761 -0.0309 0.2916 1.0000
4.750 0.7306 0.01830 0.00798 -0.0298 0.2812 1.0000
5.000 0.7519 0.01869 0.00836 -0.0287 0.2715 1.0000
5.250 0.7727 0.01912 0.00874 -0.0276 0.2632 1.0000
5.500 0.7936 0.01954 0.00916 -0.0265 0.2547 1.0000
5.750 0.8145 0.01999 0.00960 -0.0254 0.2473 1.0000
6.000 0.8353 0.02045 0.01008 -0.0243 0.2404 1.0000
6.250 0.8561 0.02093 0.01057 -0.0232 0.2345 1.0000
6.500 0.8772 0.02141 0.01110 -0.0221 0.2289 1.0000
6.750 0.8979 0.02194 0.01162 -0.0210 0.2245 1.0000
7.000 0.9193 0.02248 0.01223 -0.0200 0.2200 1.0000
7.250 0.9406 0.02302 0.01286 -0.0190 0.2157 1.0000
7.500 0.9614 0.02357 0.01349 -0.0180 0.2117 1.0000
7.750 0.9794 0.02401 0.01402 -0.0166 0.2037 1.0000
8.000 0.9937 0.02432 0.01435 -0.0147 0.1917 1.0000
8.250 1.0093 0.02472 0.01480 -0.0131 0.1827 1.0000
8.500 1.0227 0.02509 0.01521 -0.0112 0.1688 1.0000
8.750 1.0377 0.02554 0.01573 -0.0095 0.1559 1.0000
9.000 1.0523 0.02605 0.01628 -0.0078 0.1415 1.0000
9.250 1.0674 0.02663 0.01694 -0.0061 0.1205 1.0000
9.750 1.0618 0.03040 0.01996 0.0006 0.0250 1.0000
10.000 1.0637 0.03208 0.02174 0.0034 0.0205 1.0000
10.250 1.0691 0.03351 0.02333 0.0056 0.0188 1.0000
10.500 1.0742 0.03500 0.02502 0.0076 0.0178 1.0000
10.750 1.0773 0.03669 0.02691 0.0095 0.0171 1.0000
11.000 1.0776 0.03866 0.02909 0.0113 0.0164 1.0000
11.250 1.0763 0.04085 0.03148 0.0128 0.0160 1.0000
11.500 1.0726 0.04335 0.03420 0.0140 0.0157 1.0000
11.750 1.0663 0.04626 0.03731 0.0148 0.0156 1.0000
12.000 1.0546 0.04999 0.04126 0.0150 0.0153 1.0000
12.250 1.0423 0.05420 0.04568 0.0144 0.0152 1.0000
12.500 1.0251 0.05959 0.05128 0.0126 0.0152 1.0000
12.750 1.0047 0.06628 0.05820 0.0095 0.0152 1.0000
13.000 0.9817 0.07415 0.06628 0.0055 0.0153 1.0000
13.250 0.9618 0.08173 0.07405 0.0018 0.0156 1.0000
13.500 0.9408 0.08958 0.08206 -0.0019 0.0157 1.0000
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Polar data table (+)
Polar graphs
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