FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 76-MP-120 (fx76mp120-il) Reynolds number: 1,000,000 Max Cl/Cd: 173.96 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76mp120-il-1000000-n5.txt Download as CSV file: xf-fx76mp120-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.0981 0.09239 0.08932 -0.1433 0.7752 0.0067
-10.750 0.1113 0.09053 0.08745 -0.1449 0.7734 0.0070
-10.250 -0.1743 0.02118 0.01738 -0.2018 0.7630 0.0086
-10.000 -0.1533 0.01911 0.01508 -0.2033 0.7609 0.0087
-9.750 -0.1297 0.01778 0.01356 -0.2042 0.7592 0.0089
-9.500 -0.1050 0.01668 0.01229 -0.2049 0.7574 0.0090
-9.250 -0.0802 0.01549 0.01093 -0.2057 0.7555 0.0094
-9.000 -0.0539 0.01472 0.01005 -0.2062 0.7539 0.0098
-8.750 -0.0271 0.01414 0.00940 -0.2066 0.7522 0.0101
-8.500 0.0000 0.01358 0.00875 -0.2070 0.7505 0.0104
-8.250 0.0273 0.01307 0.00814 -0.2073 0.7487 0.0107
-8.000 0.0546 0.01258 0.00755 -0.2077 0.7468 0.0111
-7.750 0.0822 0.01215 0.00702 -0.2079 0.7449 0.0114
-7.500 0.1097 0.01176 0.00653 -0.2082 0.7431 0.0117
-7.250 0.1374 0.01137 0.00604 -0.2085 0.7413 0.0120
-7.000 0.1653 0.01094 0.00554 -0.2088 0.7396 0.0126
-6.750 0.1934 0.01061 0.00517 -0.2090 0.7379 0.0131
-6.500 0.2215 0.01034 0.00485 -0.2093 0.7360 0.0137
-6.250 0.2496 0.01009 0.00455 -0.2095 0.7340 0.0143
-6.000 0.2777 0.00986 0.00427 -0.2097 0.7319 0.0149
-5.750 0.3057 0.00960 0.00397 -0.2099 0.7299 0.0159
-5.500 0.3337 0.00940 0.00372 -0.2100 0.7279 0.0170
-5.250 0.3618 0.00924 0.00351 -0.2102 0.7259 0.0181
-5.000 0.3901 0.00907 0.00331 -0.2103 0.7240 0.0190
-4.750 0.4183 0.00887 0.00311 -0.2105 0.7220 0.0207
-4.500 0.4465 0.00873 0.00296 -0.2107 0.7197 0.0225
-4.250 0.4747 0.00860 0.00280 -0.2108 0.7174 0.0242
-4.000 0.5027 0.00847 0.00266 -0.2109 0.7151 0.0263
-3.750 0.5305 0.00838 0.00253 -0.2110 0.7127 0.0283
-3.500 0.5585 0.00828 0.00240 -0.2111 0.7103 0.0302
-3.250 0.5866 0.00817 0.00231 -0.2112 0.7078 0.0329
-3.000 0.6146 0.00809 0.00222 -0.2113 0.7048 0.0354
-2.750 0.6425 0.00800 0.00213 -0.2114 0.7019 0.0384
-2.500 0.6701 0.00793 0.00206 -0.2114 0.6990 0.0419
-2.000 0.7257 0.00782 0.00193 -0.2115 0.6937 0.0495
-1.750 0.7535 0.00776 0.00188 -0.2116 0.6906 0.0532
-1.500 0.7810 0.00772 0.00183 -0.2116 0.6871 0.0583
-1.250 0.8082 0.00768 0.00180 -0.2115 0.6835 0.0644
-1.000 0.8355 0.00766 0.00177 -0.2115 0.6800 0.0704
-0.750 0.8630 0.00762 0.00176 -0.2115 0.6762 0.0786
-0.500 0.8901 0.00760 0.00175 -0.2114 0.6720 0.0874
0.000 0.9438 0.00758 0.00175 -0.2112 0.6639 0.1094
0.250 0.9708 0.00756 0.00177 -0.2111 0.6592 0.1251
0.500 0.9970 0.00755 0.00180 -0.2109 0.6544 0.1487
1.000 1.0498 0.00751 0.00188 -0.2106 0.6443 0.2092
1.250 1.0751 0.00750 0.00194 -0.2102 0.6385 0.2581
1.500 1.1009 0.00746 0.00202 -0.2100 0.6324 0.3173
1.750 1.1253 0.00737 0.00213 -0.2095 0.6250 0.4257
2.000 1.1492 0.00719 0.00227 -0.2089 0.6180 0.5907
2.250 1.1717 0.00713 0.00243 -0.2080 0.6099 0.7106
2.500 1.1950 0.00717 0.00256 -0.2071 0.6022 0.7676
3.000 1.2365 0.00729 0.00282 -0.2043 0.5829 0.8679
3.250 1.2664 0.00728 0.00293 -0.2049 0.5726 1.0000
3.500 1.2884 0.00749 0.00307 -0.2039 0.5616 1.0000
3.750 1.3103 0.00769 0.00322 -0.2028 0.5503 1.0000
4.000 1.3317 0.00790 0.00338 -0.2017 0.5385 1.0000
4.250 1.3514 0.00815 0.00357 -0.2002 0.5260 1.0000
4.500 1.3681 0.00842 0.00378 -0.1981 0.5119 1.0000
4.750 1.3843 0.00872 0.00401 -0.1959 0.4978 1.0000
5.000 1.4012 0.00902 0.00425 -0.1939 0.4852 1.0000
5.500 1.4349 0.00965 0.00479 -0.1900 0.4607 1.0000
5.750 1.4516 0.00999 0.00509 -0.1881 0.4491 1.0000
6.000 1.4673 0.01038 0.00543 -0.1861 0.4370 1.0000
6.250 1.4814 0.01083 0.00583 -0.1838 0.4229 1.0000
6.500 1.4957 0.01131 0.00626 -0.1816 0.4097 1.0000
6.750 1.5109 0.01179 0.00670 -0.1797 0.3980 1.0000
7.000 1.5263 0.01230 0.00718 -0.1779 0.3861 1.0000
7.250 1.5414 0.01286 0.00772 -0.1761 0.3752 1.0000
7.500 1.5559 0.01350 0.00832 -0.1743 0.3639 1.0000
7.750 1.5706 0.01417 0.00896 -0.1726 0.3520 1.0000
8.000 1.5848 0.01493 0.00968 -0.1710 0.3386 1.0000
8.250 1.6001 0.01567 0.01041 -0.1696 0.3274 1.0000
8.500 1.6137 0.01655 0.01125 -0.1680 0.3141 1.0000
8.750 1.6279 0.01743 0.01210 -0.1666 0.3033 1.0000
9.000 1.6409 0.01841 0.01304 -0.1651 0.2907 1.0000
9.250 1.6518 0.01954 0.01410 -0.1634 0.2747 1.0000
9.500 1.6576 0.02100 0.01545 -0.1610 0.2511 1.0000
9.750 1.6603 0.02268 0.01699 -0.1584 0.2255 1.0000
10.000 1.6625 0.02438 0.01856 -0.1557 0.2028 1.0000
10.250 1.6673 0.02592 0.02002 -0.1534 0.1834 1.0000
10.500 1.6663 0.02788 0.02182 -0.1505 0.1583 1.0000
10.750 1.6685 0.02964 0.02349 -0.1480 0.1388 1.0000
11.000 1.6704 0.03148 0.02523 -0.1455 0.1214 1.0000
11.250 1.6768 0.03301 0.02672 -0.1436 0.1097 1.0000
11.500 1.6785 0.03491 0.02856 -0.1413 0.0944 1.0000
11.750 1.6822 0.03670 0.03029 -0.1393 0.0818 1.0000
12.000 1.6799 0.03902 0.03252 -0.1367 0.0638 1.0000
12.250 1.6819 0.04101 0.03447 -0.1347 0.0530 1.0000
12.500 1.6824 0.04316 0.03657 -0.1325 0.0421 1.0000
12.750 1.6830 0.04537 0.03876 -0.1305 0.0329 1.0000
13.000 1.6866 0.04736 0.04074 -0.1288 0.0268 1.0000
13.250 1.6882 0.04955 0.04294 -0.1271 0.0210 1.0000
13.500 1.6914 0.05161 0.04501 -0.1255 0.0170 1.0000
13.750 1.6952 0.05369 0.04712 -0.1241 0.0145 1.0000
14.250 1.7020 0.05798 0.05148 -0.1213 0.0102 1.0000
14.500 1.7049 0.06023 0.05377 -0.1201 0.0089 1.0000
14.750 1.7084 0.06243 0.05603 -0.1189 0.0077 1.0000
15.000 1.7098 0.06490 0.05854 -0.1177 0.0067 1.0000
15.250 1.7133 0.06717 0.06087 -0.1167 0.0061 1.0000
15.500 1.7144 0.06978 0.06354 -0.1157 0.0053 1.0000
15.750 1.7159 0.07237 0.06619 -0.1147 0.0049 1.0000
16.000 1.7180 0.07496 0.06885 -0.1140 0.0046 1.0000
16.250 1.7191 0.07767 0.07164 -0.1132 0.0043 1.0000
16.500 1.7199 0.08047 0.07450 -0.1126 0.0040 1.0000
16.750 1.7193 0.08354 0.07765 -0.1121 0.0038 1.0000
17.000 1.7186 0.08666 0.08085 -0.1116 0.0035 1.0000
17.250 1.7172 0.08994 0.08420 -0.1113 0.0033 1.0000
17.500 1.7170 0.09313 0.08747 -0.1112 0.0033 1.0000
17.750 1.7162 0.09643 0.09085 -0.1112 0.0031 1.0000
18.000 1.7150 0.09983 0.09434 -0.1112 0.0030 1.0000
18.250 1.7135 0.10334 0.09794 -0.1115 0.0029 1.0000
18.500 1.7111 0.10706 0.10174 -0.1119 0.0028 1.0000
18.750 1.7087 0.11080 0.10557 -0.1124 0.0027 1.0000
19.000 1.7066 0.11453 0.10939 -0.1130 0.0027 1.0000
19.250 1.7032 0.11850 0.11345 -0.1138 0.0026 1.0000
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