WORTMANN FX 76-120 (fx76120-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 76-120 (fx76120-il) Reynolds number: 100,000 Max Cl/Cd: 35.9 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76120-il-100000.txt Download as CSV file: xf-fx76120-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 76-120
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8039 0.08399 0.07831 -0.0358 1.0000 0.0832
-12.500 -0.8351 0.07551 0.06977 -0.0406 1.0000 0.0823
-12.250 -0.8724 0.06808 0.06220 -0.0441 1.0000 0.0814
-12.000 -0.9071 0.06243 0.05637 -0.0450 1.0000 0.0808
-11.750 -0.9358 0.05812 0.05185 -0.0436 1.0000 0.0802
-11.500 -0.9627 0.05463 0.04813 -0.0401 1.0000 0.0802
-11.250 -0.9827 0.05153 0.04474 -0.0363 1.0000 0.0809
-11.000 -0.9970 0.04840 0.04123 -0.0326 1.0000 0.0818
-10.750 -1.0069 0.04564 0.03802 -0.0288 1.0000 0.0830
-10.500 -1.0051 0.04255 0.03468 -0.0263 1.0000 0.0848
-10.250 -0.9918 0.04044 0.03252 -0.0248 1.0000 0.0872
-10.000 -0.9804 0.03863 0.03056 -0.0228 1.0000 0.0901
-9.750 -0.9724 0.03676 0.02836 -0.0202 1.0000 0.0936
-9.500 -0.9637 0.03467 0.02589 -0.0175 1.0000 0.0966
-9.250 -0.9441 0.03296 0.02430 -0.0165 1.0000 0.1008
-9.000 -0.9295 0.03158 0.02270 -0.0145 1.0000 0.1058
-8.750 -0.9138 0.02990 0.02083 -0.0126 1.0000 0.1109
-8.500 -0.8951 0.02873 0.01973 -0.0112 1.0000 0.1171
-8.250 -0.8787 0.02738 0.01817 -0.0092 1.0000 0.1243
-8.000 -0.8608 0.02642 0.01730 -0.0076 1.0000 0.1329
-7.750 -0.8433 0.02530 0.01619 -0.0059 1.0000 0.1426
-7.500 -0.8268 0.02434 0.01519 -0.0039 1.0000 0.1546
-7.250 -0.8104 0.02348 0.01433 -0.0018 1.0000 0.1687
-7.000 -0.7944 0.02271 0.01362 0.0002 1.0000 0.1848
-6.750 -0.7784 0.02202 0.01299 0.0023 1.0000 0.2022
-6.500 -0.7624 0.02140 0.01243 0.0045 1.0000 0.2206
-6.250 -0.7461 0.02084 0.01189 0.0066 1.0000 0.2395
-6.000 -0.7296 0.02033 0.01137 0.0086 1.0000 0.2585
-5.750 -0.7127 0.01986 0.01087 0.0106 1.0000 0.2770
-5.500 -0.6950 0.01936 0.01043 0.0125 1.0000 0.2949
-5.250 -0.6769 0.01888 0.01003 0.0143 1.0000 0.3129
-5.000 -0.6587 0.01843 0.00965 0.0160 1.0000 0.3310
-4.750 -0.6402 0.01799 0.00928 0.0178 1.0000 0.3497
-4.500 -0.6218 0.01758 0.00894 0.0195 1.0000 0.3696
-4.250 -0.6033 0.01718 0.00859 0.0213 1.0000 0.3911
-4.000 -0.5846 0.01676 0.00829 0.0230 1.0000 0.4132
-3.750 -0.5661 0.01637 0.00803 0.0247 1.0000 0.4381
-3.500 -0.5476 0.01597 0.00780 0.0264 1.0000 0.4654
-3.250 -0.5296 0.01560 0.00761 0.0283 1.0000 0.4969
-3.000 -0.5120 0.01526 0.00749 0.0303 1.0000 0.5330
-2.750 -0.4950 0.01496 0.00740 0.0325 1.0000 0.5754
-2.500 -0.4781 0.01468 0.00741 0.0347 1.0000 0.6218
-2.250 -0.4610 0.01449 0.00749 0.0371 1.0000 0.6729
-2.000 -0.4431 0.01441 0.00765 0.0395 1.0000 0.7277
-1.750 -0.4222 0.01449 0.00794 0.0415 1.0000 0.7811
-1.500 -0.3964 0.01474 0.00832 0.0425 1.0000 0.8320
-1.250 -0.3642 0.01514 0.00877 0.0423 1.0000 0.8786
-1.000 -0.3148 0.01576 0.00937 0.0387 1.0000 0.9142
-0.750 -0.2553 0.01646 0.01001 0.0328 1.0000 0.9410
-0.500 -0.1795 0.01716 0.01063 0.0237 0.9974 0.9577
-0.250 -0.0903 0.01768 0.01110 0.0120 0.9889 0.9694
0.000 0.0003 0.01787 0.01127 -0.0001 0.9802 0.9802
0.250 0.0898 0.01769 0.01111 -0.0119 0.9695 0.9889
0.500 0.1794 0.01716 0.01064 -0.0237 0.9576 0.9972
0.750 0.2553 0.01646 0.01000 -0.0329 0.9410 1.0000
1.000 0.3143 0.01577 0.00938 -0.0386 0.9145 1.0000
1.250 0.3640 0.01514 0.00877 -0.0423 0.8787 1.0000
1.500 0.3963 0.01474 0.00832 -0.0426 0.8321 1.0000
1.750 0.4222 0.01449 0.00793 -0.0414 0.7808 1.0000
2.000 0.4431 0.01441 0.00764 -0.0395 0.7274 1.0000
2.250 0.4609 0.01449 0.00748 -0.0371 0.6727 1.0000
2.500 0.4780 0.01468 0.00741 -0.0347 0.6215 1.0000
2.750 0.4950 0.01495 0.00740 -0.0324 0.5753 1.0000
3.000 0.5120 0.01526 0.00748 -0.0303 0.5329 1.0000
3.250 0.5296 0.01560 0.00761 -0.0283 0.4971 1.0000
3.500 0.5476 0.01597 0.00780 -0.0265 0.4656 1.0000
3.750 0.5660 0.01636 0.00803 -0.0247 0.4382 1.0000
4.000 0.5846 0.01675 0.00829 -0.0230 0.4133 1.0000
4.250 0.6033 0.01718 0.00859 -0.0213 0.3912 1.0000
4.500 0.6218 0.01758 0.00894 -0.0195 0.3697 1.0000
4.750 0.6402 0.01799 0.00929 -0.0178 0.3498 1.0000
5.000 0.6586 0.01843 0.00964 -0.0160 0.3311 1.0000
5.250 0.6770 0.01888 0.01004 -0.0143 0.3130 1.0000
5.500 0.6950 0.01936 0.01043 -0.0125 0.2950 1.0000
5.750 0.7127 0.01985 0.01086 -0.0106 0.2771 1.0000
6.000 0.7296 0.02033 0.01137 -0.0086 0.2586 1.0000
6.250 0.7461 0.02084 0.01189 -0.0066 0.2396 1.0000
6.500 0.7625 0.02141 0.01244 -0.0045 0.2209 1.0000
6.750 0.7784 0.02202 0.01299 -0.0023 0.2022 1.0000
7.000 0.7944 0.02271 0.01362 -0.0002 0.1847 1.0000
7.250 0.8104 0.02348 0.01432 0.0018 0.1687 1.0000
7.500 0.8268 0.02433 0.01518 0.0039 0.1547 1.0000
7.750 0.8433 0.02529 0.01617 0.0059 0.1425 1.0000
8.000 0.8609 0.02642 0.01728 0.0076 0.1330 1.0000
8.250 0.8788 0.02738 0.01819 0.0092 0.1244 1.0000
8.500 0.8952 0.02873 0.01973 0.0112 0.1171 1.0000
8.750 0.9138 0.02989 0.02083 0.0126 0.1109 1.0000
9.000 0.9294 0.03157 0.02270 0.0145 0.1057 1.0000
9.250 0.9441 0.03292 0.02424 0.0165 0.1006 1.0000
9.500 0.9638 0.03467 0.02588 0.0175 0.0966 1.0000
9.750 0.9723 0.03674 0.02835 0.0202 0.0935 1.0000
10.000 0.9804 0.03866 0.03059 0.0228 0.0902 1.0000
10.250 0.9919 0.04045 0.03252 0.0248 0.0872 1.0000
10.500 1.0064 0.04258 0.03466 0.0261 0.0845 1.0000
10.750 1.0069 0.04562 0.03801 0.0288 0.0829 1.0000
11.000 0.9967 0.04840 0.04124 0.0327 0.0817 1.0000
11.250 0.9832 0.05149 0.04470 0.0363 0.0808 1.0000
11.500 0.9625 0.05462 0.04812 0.0401 0.0801 1.0000
11.750 0.9369 0.05811 0.05184 0.0435 0.0803 1.0000
12.000 0.9059 0.06248 0.05643 0.0450 0.0806 1.0000
12.250 0.8707 0.06821 0.06233 0.0439 0.0812 1.0000
12.500 0.8340 0.07573 0.06999 0.0402 0.0823 1.0000
12.750 0.8038 0.08414 0.07847 0.0355 0.0832 1.0000
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