FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 76-MP-120 (fx76mp120-il) Reynolds number: 500,000 Max Cl/Cd: 141.45 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76mp120-il-500000-n5.txt Download as CSV file: xf-fx76mp120-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 76-MP-120
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.1597 0.08841 0.08464 -0.1525 0.7948 0.0106
-10.000 0.1672 0.08554 0.08177 -0.1539 0.7927 0.0106
-9.750 0.1737 0.08247 0.07871 -0.1554 0.7906 0.0108
-9.500 0.1808 0.07958 0.07580 -0.1568 0.7885 0.0106
-8.500 0.0051 0.02259 0.01819 -0.2004 0.7728 0.0125
-8.250 0.0288 0.02067 0.01601 -0.2022 0.7709 0.0128
-8.000 0.0533 0.01919 0.01431 -0.2033 0.7690 0.0132
-7.750 0.0785 0.01792 0.01282 -0.2042 0.7670 0.0137
-7.500 0.1045 0.01679 0.01147 -0.2049 0.7651 0.0142
-7.250 0.1311 0.01587 0.01034 -0.2055 0.7630 0.0147
-7.000 0.1581 0.01506 0.00934 -0.2060 0.7610 0.0153
-6.750 0.1855 0.01453 0.00872 -0.2064 0.7591 0.0160
-6.500 0.2134 0.01416 0.00826 -0.2068 0.7574 0.0169
-6.250 0.2416 0.01371 0.00767 -0.2072 0.7558 0.0177
-6.000 0.2691 0.01323 0.00708 -0.2075 0.7539 0.0185
-5.750 0.2966 0.01276 0.00651 -0.2077 0.7517 0.0194
-5.500 0.3242 0.01242 0.00612 -0.2079 0.7496 0.0204
-5.250 0.3520 0.01217 0.00582 -0.2081 0.7475 0.0219
-5.000 0.3800 0.01190 0.00547 -0.2082 0.7454 0.0234
-4.750 0.4081 0.01159 0.00510 -0.2085 0.7434 0.0250
-4.500 0.4365 0.01140 0.00485 -0.2087 0.7416 0.0268
-4.250 0.4646 0.01121 0.00459 -0.2089 0.7396 0.0287
-4.000 0.4921 0.01098 0.00436 -0.2090 0.7373 0.0309
-3.750 0.5197 0.01084 0.00421 -0.2090 0.7349 0.0336
-3.500 0.5474 0.01072 0.00404 -0.2091 0.7325 0.0359
-3.250 0.5753 0.01053 0.00385 -0.2092 0.7302 0.0391
-3.000 0.6034 0.01042 0.00370 -0.2093 0.7280 0.0424
-2.750 0.6318 0.01031 0.00353 -0.2095 0.7258 0.0456
-2.500 0.6589 0.01019 0.00344 -0.2095 0.7231 0.0497
-2.250 0.6861 0.01010 0.00333 -0.2094 0.7201 0.0533
-2.000 0.7135 0.00998 0.00322 -0.2094 0.7171 0.0581
-1.750 0.7412 0.00990 0.00314 -0.2095 0.7144 0.0636
-1.500 0.7691 0.00984 0.00303 -0.2096 0.7119 0.0690
-1.250 0.7964 0.00977 0.00299 -0.2095 0.7090 0.0770
-1.000 0.8233 0.00972 0.00296 -0.2094 0.7058 0.0849
-0.750 0.8503 0.00967 0.00293 -0.2094 0.7025 0.0941
-0.500 0.8775 0.00961 0.00289 -0.2093 0.6992 0.1070
-0.250 0.9050 0.00957 0.00285 -0.2093 0.6961 0.1223
0.000 0.9312 0.00953 0.00288 -0.2091 0.6921 0.1430
0.250 0.9576 0.00947 0.00289 -0.2090 0.6880 0.1715
0.500 0.9843 0.00941 0.00291 -0.2089 0.6843 0.2089
0.750 1.0109 0.00933 0.00294 -0.2088 0.6807 0.2670
1.000 1.0366 0.00921 0.00303 -0.2086 0.6761 0.3469
1.250 1.0619 0.00898 0.00313 -0.2084 0.6714 0.5007
1.500 1.0846 0.00868 0.00331 -0.2075 0.6673 0.7163
1.750 1.1073 0.00864 0.00344 -0.2064 0.6624 0.7933
2.000 1.1306 0.00865 0.00350 -0.2054 0.6570 0.8322
2.250 1.1522 0.00863 0.00354 -0.2041 0.6520 0.8821
2.500 1.1838 0.00856 0.00357 -0.2050 0.6459 1.0000
2.750 1.2087 0.00867 0.00363 -0.2045 0.6392 1.0000
3.000 1.2336 0.00879 0.00371 -0.2040 0.6326 1.0000
3.250 1.2576 0.00892 0.00381 -0.2034 0.6252 1.0000
3.500 1.2815 0.00906 0.00392 -0.2028 0.6175 1.0000
3.750 1.3042 0.00922 0.00404 -0.2018 0.6090 1.0000
4.000 1.3268 0.00938 0.00417 -0.2010 0.5997 1.0000
4.250 1.3482 0.00958 0.00433 -0.1998 0.5906 1.0000
4.500 1.3687 0.00979 0.00451 -0.1985 0.5802 1.0000
4.750 1.3886 0.01001 0.00469 -0.1971 0.5696 1.0000
5.000 1.4053 0.01026 0.00491 -0.1950 0.5585 1.0000
5.250 1.4201 0.01057 0.00516 -0.1926 0.5460 1.0000
5.500 1.4350 0.01090 0.00544 -0.1902 0.5337 1.0000
5.750 1.4493 0.01126 0.00576 -0.1878 0.5204 1.0000
6.000 1.4635 0.01164 0.00610 -0.1854 0.5079 1.0000
6.250 1.4774 0.01205 0.00649 -0.1830 0.4964 1.0000
6.500 1.4900 0.01253 0.00694 -0.1805 0.4845 1.0000
6.750 1.5010 0.01309 0.00745 -0.1777 0.4715 1.0000
7.000 1.5128 0.01367 0.00800 -0.1753 0.4588 1.0000
7.250 1.5235 0.01434 0.00863 -0.1727 0.4451 1.0000
7.500 1.5348 0.01503 0.00931 -0.1703 0.4324 1.0000
7.750 1.5463 0.01576 0.01002 -0.1681 0.4209 1.0000
8.000 1.5572 0.01657 0.01081 -0.1658 0.4095 1.0000
8.250 1.5673 0.01747 0.01168 -0.1636 0.3969 1.0000
8.500 1.5787 0.01834 0.01255 -0.1616 0.3847 1.0000
8.750 1.5902 0.01925 0.01345 -0.1597 0.3736 1.0000
9.000 1.5996 0.02031 0.01448 -0.1576 0.3607 1.0000
9.250 1.6088 0.02141 0.01556 -0.1555 0.3481 1.0000
9.500 1.6184 0.02251 0.01665 -0.1536 0.3366 1.0000
9.750 1.6279 0.02364 0.01777 -0.1517 0.3238 1.0000
10.000 1.6371 0.02481 0.01894 -0.1497 0.3117 1.0000
10.250 1.6439 0.02617 0.02026 -0.1476 0.2972 1.0000
10.500 1.6476 0.02777 0.02179 -0.1452 0.2793 1.0000
10.750 1.6494 0.02954 0.02348 -0.1427 0.2604 1.0000
11.000 1.6518 0.03133 0.02519 -0.1404 0.2401 1.0000
11.250 1.6513 0.03338 0.02712 -0.1379 0.2182 1.0000
11.500 1.6522 0.03538 0.02903 -0.1356 0.1973 1.0000
11.750 1.6528 0.03748 0.03104 -0.1334 0.1777 1.0000
12.000 1.6538 0.03959 0.03306 -0.1313 0.1599 1.0000
12.250 1.6543 0.04180 0.03519 -0.1293 0.1410 1.0000
12.500 1.6555 0.04401 0.03733 -0.1275 0.1249 1.0000
12.750 1.6554 0.04638 0.03963 -0.1256 0.1086 1.0000
13.000 1.6562 0.04875 0.04196 -0.1239 0.0948 1.0000
13.250 1.6554 0.05131 0.04446 -0.1222 0.0795 1.0000
13.500 1.6538 0.05403 0.04713 -0.1206 0.0654 1.0000
13.750 1.6528 0.05676 0.04984 -0.1192 0.0540 1.0000
14.000 1.6515 0.05959 0.05265 -0.1178 0.0438 1.0000
14.250 1.6491 0.06260 0.05564 -0.1166 0.0345 1.0000
14.500 1.6482 0.06553 0.05858 -0.1155 0.0278 1.0000
14.750 1.6477 0.06849 0.06157 -0.1146 0.0224 1.0000
15.000 1.6473 0.07149 0.06460 -0.1138 0.0184 1.0000
15.250 1.6463 0.07464 0.06781 -0.1131 0.0153 1.0000
15.500 1.6464 0.07769 0.07092 -0.1125 0.0129 1.0000
15.750 1.6468 0.08076 0.07407 -0.1120 0.0114 1.0000
16.000 1.6467 0.08398 0.07736 -0.1117 0.0101 1.0000
16.500 1.6459 0.09061 0.08416 -0.1114 0.0083 1.0000
16.750 1.6448 0.09410 0.08774 -0.1114 0.0076 1.0000
17.000 1.6429 0.09775 0.09148 -0.1115 0.0071 1.0000
17.250 1.6403 0.10156 0.09539 -0.1118 0.0067 1.0000
17.500 1.6393 0.10517 0.09912 -0.1122 0.0064 1.0000
17.750 1.6373 0.10898 0.10304 -0.1127 0.0060 1.0000
18.000 1.6347 0.11291 0.10708 -0.1134 0.0057 1.0000
18.250 1.6319 0.11692 0.11119 -0.1142 0.0055 1.0000
18.500 1.6282 0.12107 0.11544 -0.1151 0.0052 1.0000
18.750 1.6237 0.12541 0.11988 -0.1163 0.0050 1.0000
19.000 1.6186 0.12990 0.12448 -0.1176 0.0049 1.0000
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