SG6042 (sg6042-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6042 (sg6042-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.88 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6042-il-1000000-n5.txt Download as CSV file: xf-sg6042-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6042
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3787 0.13640 0.13460 -0.0327 0.9996 0.0045
-11.000 -0.6315 0.02749 0.02476 -0.1171 0.9741 0.0049
-10.750 -0.6157 0.02473 0.02173 -0.1183 0.9697 0.0050
-10.500 -0.5951 0.02307 0.01991 -0.1189 0.9650 0.0051
-10.250 -0.5702 0.02125 0.01788 -0.1203 0.9620 0.0052
-10.000 -0.5414 0.02018 0.01669 -0.1217 0.9600 0.0053
-9.750 -0.5208 0.01923 0.01562 -0.1212 0.9533 0.0054
-9.500 -0.4942 0.01796 0.01416 -0.1221 0.9492 0.0056
-9.250 -0.4651 0.01701 0.01307 -0.1232 0.9460 0.0058
-9.000 -0.4402 0.01607 0.01198 -0.1233 0.9399 0.0059
-8.750 -0.4116 0.01529 0.01106 -0.1240 0.9350 0.0062
-8.500 -0.3837 0.01458 0.01020 -0.1245 0.9298 0.0064
-8.250 -0.3566 0.01399 0.00947 -0.1247 0.9234 0.0066
-8.000 -0.3290 0.01330 0.00864 -0.1251 0.9178 0.0068
-7.750 -0.3035 0.01270 0.00796 -0.1250 0.9111 0.0071
-7.500 -0.2764 0.01228 0.00745 -0.1250 0.9050 0.0073
-7.250 -0.2497 0.01192 0.00702 -0.1250 0.8992 0.0076
-7.000 -0.2231 0.01156 0.00659 -0.1249 0.8930 0.0079
-6.750 -0.1963 0.01118 0.00611 -0.1248 0.8873 0.0082
-6.500 -0.1700 0.01079 0.00564 -0.1246 0.8812 0.0085
-6.250 -0.1433 0.01047 0.00522 -0.1244 0.8754 0.0088
-6.000 -0.1164 0.01020 0.00488 -0.1243 0.8701 0.0091
-5.750 -0.0902 0.00977 0.00438 -0.1240 0.8645 0.0095
-5.500 -0.0634 0.00948 0.00405 -0.1239 0.8593 0.0099
-5.250 -0.0363 0.00927 0.00381 -0.1238 0.8545 0.0105
-5.000 -0.0093 0.00903 0.00352 -0.1236 0.8492 0.0110
-4.750 0.0178 0.00880 0.00323 -0.1235 0.8442 0.0114
-4.500 0.0451 0.00859 0.00298 -0.1234 0.8394 0.0118
-4.250 0.0722 0.00835 0.00270 -0.1232 0.8339 0.0122
-4.000 0.0992 0.00812 0.00242 -0.1230 0.8284 0.0130
-3.750 0.1266 0.00795 0.00223 -0.1229 0.8232 0.0139
-3.500 0.1541 0.00780 0.00205 -0.1228 0.8176 0.0146
-3.000 0.2091 0.00753 0.00171 -0.1226 0.8072 0.0166
-2.750 0.2365 0.00741 0.00158 -0.1224 0.8008 0.0186
-2.500 0.2637 0.00727 0.00146 -0.1223 0.7942 0.0266
-2.250 0.2911 0.00713 0.00137 -0.1222 0.7872 0.0410
-2.000 0.3184 0.00705 0.00129 -0.1220 0.7808 0.0521
-1.750 0.3459 0.00695 0.00122 -0.1219 0.7736 0.0660
-1.500 0.3729 0.00688 0.00116 -0.1217 0.7650 0.0810
-1.250 0.3998 0.00678 0.00111 -0.1215 0.7543 0.1076
-1.000 0.4266 0.00665 0.00106 -0.1213 0.7433 0.1495
-0.750 0.4530 0.00647 0.00103 -0.1211 0.7324 0.2171
-0.500 0.4792 0.00624 0.00101 -0.1209 0.7205 0.3120
-0.250 0.5051 0.00608 0.00101 -0.1206 0.7061 0.3931
0.000 0.5303 0.00584 0.00103 -0.1202 0.6894 0.5167
0.250 0.5558 0.00575 0.00108 -0.1198 0.6719 0.5936
0.500 0.5813 0.00579 0.00114 -0.1192 0.6520 0.6353
0.750 0.6058 0.00585 0.00121 -0.1185 0.6283 0.6801
1.000 0.6300 0.00595 0.00130 -0.1177 0.6020 0.7196
1.250 0.6546 0.00604 0.00139 -0.1169 0.5792 0.7529
1.500 0.6786 0.00617 0.00149 -0.1161 0.5543 0.7831
1.750 0.7020 0.00634 0.00160 -0.1151 0.5245 0.8118
2.000 0.7245 0.00655 0.00174 -0.1140 0.4895 0.8391
2.250 0.7465 0.00679 0.00188 -0.1128 0.4531 0.8626
2.500 0.7688 0.00700 0.00201 -0.1116 0.4233 0.8861
2.750 0.7901 0.00715 0.00214 -0.1101 0.3998 0.9176
3.000 0.8161 0.00736 0.00227 -0.1098 0.3684 0.9736
3.250 0.8423 0.00765 0.00242 -0.1096 0.3394 1.0000
3.500 0.8665 0.00793 0.00258 -0.1090 0.3145 1.0000
3.750 0.8900 0.00825 0.00276 -0.1082 0.2862 1.0000
4.000 0.9133 0.00858 0.00296 -0.1074 0.2592 1.0000
4.250 0.9366 0.00891 0.00316 -0.1067 0.2340 1.0000
4.500 0.9599 0.00924 0.00337 -0.1059 0.2104 1.0000
5.000 1.0070 0.00985 0.00379 -0.1044 0.1748 1.0000
5.250 1.0302 0.01016 0.00403 -0.1036 0.1577 1.0000
5.500 1.0538 0.01044 0.00425 -0.1029 0.1454 1.0000
5.750 1.0771 0.01074 0.00448 -0.1022 0.1337 1.0000
6.000 1.1002 0.01104 0.00473 -0.1014 0.1223 1.0000
6.250 1.1231 0.01134 0.00499 -0.1005 0.1116 1.0000
6.500 1.1460 0.01163 0.00524 -0.0997 0.1033 1.0000
6.750 1.1684 0.01195 0.00552 -0.0988 0.0953 1.0000
7.000 1.1910 0.01224 0.00580 -0.0979 0.0886 1.0000
7.250 1.2126 0.01258 0.00610 -0.0969 0.0809 1.0000
7.500 1.2341 0.01291 0.00640 -0.0959 0.0740 1.0000
7.750 1.2545 0.01324 0.00672 -0.0946 0.0678 1.0000
8.000 1.2746 0.01357 0.00704 -0.0933 0.0631 1.0000
8.250 1.2938 0.01394 0.00738 -0.0918 0.0577 1.0000
8.500 1.3132 0.01429 0.00773 -0.0904 0.0536 1.0000
8.750 1.3317 0.01470 0.00813 -0.0889 0.0491 1.0000
9.000 1.3511 0.01504 0.00849 -0.0875 0.0466 1.0000
9.250 1.3697 0.01544 0.00889 -0.0860 0.0436 1.0000
9.500 1.3874 0.01590 0.00934 -0.0844 0.0401 1.0000
9.750 1.4059 0.01629 0.00977 -0.0830 0.0379 1.0000
10.000 1.4235 0.01674 0.01023 -0.0814 0.0354 1.0000
10.250 1.4401 0.01726 0.01075 -0.0797 0.0327 1.0000
10.500 1.4573 0.01772 0.01125 -0.0782 0.0310 1.0000
10.750 1.4740 0.01822 0.01178 -0.0766 0.0290 1.0000
11.000 1.4891 0.01883 0.01239 -0.0749 0.0266 1.0000
11.250 1.5048 0.01940 0.01300 -0.0732 0.0250 1.0000
11.500 1.5199 0.02002 0.01364 -0.0715 0.0232 1.0000
11.750 1.5338 0.02072 0.01436 -0.0697 0.0213 1.0000
12.000 1.5473 0.02144 0.01512 -0.0680 0.0195 1.0000
12.250 1.5608 0.02218 0.01590 -0.0662 0.0182 1.0000
12.500 1.5727 0.02304 0.01679 -0.0644 0.0167 1.0000
12.750 1.5851 0.02388 0.01767 -0.0627 0.0158 1.0000
13.000 1.5976 0.02473 0.01859 -0.0610 0.0152 1.0000
13.250 1.6090 0.02567 0.01958 -0.0593 0.0144 1.0000
13.500 1.6194 0.02670 0.02066 -0.0576 0.0138 1.0000
13.750 1.6285 0.02787 0.02187 -0.0558 0.0128 1.0000
14.000 1.6386 0.02897 0.02305 -0.0543 0.0123 1.0000
14.250 1.6481 0.03013 0.02429 -0.0528 0.0119 1.0000
14.500 1.6568 0.03140 0.02563 -0.0513 0.0114 1.0000
14.750 1.6644 0.03280 0.02709 -0.0498 0.0109 1.0000
15.000 1.6710 0.03432 0.02867 -0.0483 0.0104 1.0000
15.250 1.6762 0.03600 0.03042 -0.0469 0.0099 1.0000
15.500 1.6818 0.03770 0.03220 -0.0457 0.0096 1.0000
15.750 1.6874 0.03945 0.03404 -0.0446 0.0093 1.0000
16.000 1.6917 0.04137 0.03606 -0.0436 0.0091 1.0000
16.250 1.6955 0.04343 0.03820 -0.0427 0.0088 1.0000
16.500 1.6981 0.04569 0.04055 -0.0420 0.0084 1.0000
16.750 1.6995 0.04817 0.04311 -0.0414 0.0081 1.0000
17.000 1.6995 0.05089 0.04592 -0.0409 0.0079 1.0000
17.250 1.6982 0.05389 0.04902 -0.0407 0.0076 1.0000
17.500 1.6960 0.05714 0.05236 -0.0407 0.0072 1.0000
17.750 1.6943 0.06045 0.05578 -0.0410 0.0071 1.0000
18.000 1.6912 0.06405 0.05950 -0.0415 0.0070 1.0000
18.250 1.6871 0.06794 0.06351 -0.0423 0.0068 1.0000
18.500 1.6811 0.07228 0.06797 -0.0434 0.0066 1.0000
18.750 1.6735 0.07702 0.07282 -0.0449 0.0064 1.0000
19.000 1.6642 0.08216 0.07809 -0.0467 0.0062 1.0000
19.250 1.6526 0.08789 0.08395 -0.0490 0.0061 1.0000
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Polar data table (+)
Polar graphs
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