OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF102 AIRFOIL (oaf102-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.04 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf102-il-1000000.txt Download as CSV file: xf-oaf102-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: OAF102 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7973 0.11481 0.11296 -0.0019 1.0000 0.0096
-14.250 -0.8267 0.10389 0.10194 -0.0078 1.0000 0.0094
-14.000 -0.8474 0.09520 0.09316 -0.0127 1.0000 0.0094
-13.750 -0.8643 0.08750 0.08538 -0.0173 1.0000 0.0093
-13.500 -0.8812 0.08002 0.07782 -0.0220 1.0000 0.0093
-13.250 -0.8979 0.07293 0.07065 -0.0267 1.0000 0.0093
-13.000 -0.9224 0.06472 0.06233 -0.0325 1.0000 0.0092
-12.750 -0.9479 0.05655 0.05405 -0.0387 1.0000 0.0092
-12.500 -0.9703 0.04841 0.04579 -0.0461 1.0000 0.0092
-12.250 -0.9698 0.03950 0.03668 -0.0593 1.0000 0.0092
-12.000 -0.9466 0.02949 0.02624 -0.0782 1.0000 0.0093
-11.750 -0.9230 0.02477 0.02119 -0.0854 1.0000 0.0097
-11.500 -0.8958 0.02293 0.01921 -0.0881 1.0000 0.0101
-11.250 -0.8677 0.02171 0.01790 -0.0900 1.0000 0.0104
-11.000 -0.8393 0.02073 0.01683 -0.0915 1.0000 0.0108
-10.750 -0.8104 0.01981 0.01582 -0.0929 1.0000 0.0112
-10.500 -0.7812 0.01889 0.01479 -0.0943 1.0000 0.0116
-10.250 -0.7516 0.01801 0.01380 -0.0956 1.0000 0.0119
-10.000 -0.7219 0.01736 0.01306 -0.0967 1.0000 0.0122
-9.750 -0.6906 0.01566 0.01120 -0.0991 1.0000 0.0130
-9.500 -0.6600 0.01495 0.01042 -0.1003 1.0000 0.0137
-9.250 -0.6295 0.01440 0.00982 -0.1014 1.0000 0.0144
-9.000 -0.5973 0.01389 0.00925 -0.1028 0.9894 0.0152
-8.750 -0.5655 0.01353 0.00881 -0.1039 0.9755 0.0158
-8.500 -0.5359 0.01270 0.00786 -0.1048 0.9627 0.0171
-8.250 -0.5086 0.01235 0.00746 -0.1049 0.9508 0.0182
-8.000 -0.4813 0.01209 0.00713 -0.1048 0.9402 0.0194
-7.750 -0.4535 0.01189 0.00687 -0.1048 0.9299 0.0203
-7.500 -0.4237 0.01128 0.00617 -0.1055 0.9205 0.0227
-7.250 -0.3952 0.01103 0.00586 -0.1057 0.9109 0.0245
-7.000 -0.3661 0.01083 0.00559 -0.1060 0.9010 0.0259
-6.750 -0.3361 0.01038 0.00508 -0.1066 0.8918 0.0296
-6.500 -0.3070 0.01020 0.00483 -0.1069 0.8820 0.0322
-6.250 -0.2767 0.00985 0.00445 -0.1075 0.8722 0.0370
-6.000 -0.2472 0.00967 0.00421 -0.1078 0.8628 0.0409
-5.750 -0.2171 0.00938 0.00390 -0.1084 0.8530 0.0490
-5.500 -0.1869 0.00913 0.00365 -0.1089 0.8433 0.0587
-5.250 -0.1569 0.00891 0.00342 -0.1094 0.8338 0.0718
-5.000 -0.1268 0.00868 0.00321 -0.1099 0.8237 0.0887
-4.750 -0.0966 0.00846 0.00302 -0.1105 0.8140 0.1080
-4.500 -0.0667 0.00830 0.00286 -0.1110 0.8044 0.1267
-4.250 -0.0366 0.00814 0.00273 -0.1115 0.7950 0.1449
-4.000 -0.0066 0.00799 0.00262 -0.1119 0.7867 0.1669
-3.750 0.0233 0.00790 0.00252 -0.1124 0.7785 0.1840
-3.500 0.0532 0.00781 0.00244 -0.1128 0.7713 0.1984
-3.250 0.0831 0.00773 0.00236 -0.1131 0.7639 0.2119
-3.000 0.1130 0.00766 0.00229 -0.1135 0.7573 0.2256
-2.750 0.1429 0.00759 0.00223 -0.1139 0.7503 0.2399
-2.500 0.1727 0.00754 0.00218 -0.1143 0.7438 0.2553
-2.250 0.2026 0.00747 0.00215 -0.1147 0.7371 0.2712
-2.000 0.2324 0.00744 0.00211 -0.1150 0.7308 0.2872
-1.750 0.2622 0.00739 0.00209 -0.1154 0.7250 0.3030
-1.500 0.2920 0.00736 0.00208 -0.1157 0.7189 0.3177
-1.250 0.3216 0.00735 0.00207 -0.1160 0.7128 0.3321
-1.000 0.3514 0.00731 0.00207 -0.1164 0.7062 0.3459
-0.750 0.3810 0.00732 0.00207 -0.1166 0.7000 0.3586
-0.500 0.4107 0.00730 0.00208 -0.1169 0.6943 0.3716
-0.250 0.4403 0.00730 0.00209 -0.1172 0.6883 0.3843
0.000 0.4699 0.00732 0.00212 -0.1175 0.6828 0.3968
0.250 0.4996 0.00730 0.00215 -0.1178 0.6771 0.4102
0.500 0.5291 0.00732 0.00218 -0.1181 0.6712 0.4228
0.750 0.5586 0.00733 0.00222 -0.1184 0.6657 0.4338
1.250 0.6176 0.00737 0.00231 -0.1189 0.6539 0.4566
1.500 0.6472 0.00737 0.00236 -0.1192 0.6480 0.4684
1.750 0.6767 0.00739 0.00242 -0.1195 0.6415 0.4807
2.000 0.7061 0.00741 0.00248 -0.1197 0.6322 0.4939
2.250 0.7351 0.00747 0.00250 -0.1199 0.6101 0.5085
2.500 0.7643 0.00754 0.00255 -0.1201 0.5859 0.5254
2.750 0.7934 0.00762 0.00264 -0.1204 0.5661 0.5449
3.000 0.8226 0.00771 0.00273 -0.1206 0.5466 0.5682
3.250 0.8517 0.00782 0.00285 -0.1209 0.5209 0.5999
3.500 0.8807 0.00797 0.00302 -0.1213 0.4880 0.6495
3.750 0.9091 0.00804 0.00329 -0.1216 0.4426 0.7959
4.000 0.9294 0.00815 0.00343 -0.1200 0.3742 1.0000
4.250 0.9550 0.00941 0.00401 -0.1203 0.2395 1.0000
4.500 0.9804 0.01053 0.00460 -0.1204 0.1345 1.0000
4.750 1.0069 0.01125 0.00504 -0.1205 0.0816 1.0000
5.000 1.0340 0.01174 0.00538 -0.1205 0.0577 1.0000
5.250 1.0613 0.01215 0.00572 -0.1205 0.0450 1.0000
5.500 1.0885 0.01251 0.00604 -0.1205 0.0386 1.0000
5.750 1.1157 0.01287 0.00639 -0.1204 0.0338 1.0000
6.000 1.1424 0.01329 0.00677 -0.1203 0.0293 1.0000
6.250 1.1692 0.01367 0.00717 -0.1202 0.0269 1.0000
6.500 1.1959 0.01402 0.00753 -0.1201 0.0249 1.0000
6.750 1.2213 0.01460 0.00811 -0.1197 0.0223 1.0000
7.000 1.2473 0.01499 0.00853 -0.1195 0.0211 1.0000
7.250 1.2733 0.01537 0.00892 -0.1193 0.0199 1.0000
7.500 1.2987 0.01580 0.00936 -0.1189 0.0187 1.0000
7.750 1.3220 0.01654 0.01012 -0.1183 0.0173 1.0000
8.000 1.3456 0.01717 0.01081 -0.1177 0.0166 1.0000
8.250 1.3700 0.01763 0.01131 -0.1172 0.0160 1.0000
8.500 1.3937 0.01816 0.01188 -0.1166 0.0153 1.0000
8.750 1.4170 0.01869 0.01244 -0.1160 0.0146 1.0000
9.000 1.4396 0.01927 0.01303 -0.1153 0.0140 1.0000
9.250 1.4564 0.02048 0.01430 -0.1137 0.0131 1.0000
9.500 1.4761 0.02128 0.01517 -0.1125 0.0128 1.0000
9.750 1.4968 0.02190 0.01586 -0.1115 0.0124 1.0000
10.000 1.5162 0.02261 0.01663 -0.1103 0.0121 1.0000
10.250 1.5342 0.02337 0.01746 -0.1088 0.0117 1.0000
10.500 1.5512 0.02415 0.01829 -0.1073 0.0113 1.0000
10.750 1.5669 0.02495 0.01914 -0.1056 0.0110 1.0000
11.000 1.5810 0.02581 0.02005 -0.1036 0.0107 1.0000
11.250 1.5924 0.02681 0.02112 -0.1013 0.0105 1.0000
11.500 1.5956 0.02818 0.02257 -0.0979 0.0102 1.0000
11.750 1.5931 0.03031 0.02482 -0.0942 0.0099 1.0000
12.000 1.5929 0.03251 0.02718 -0.0911 0.0097 1.0000
12.250 1.6038 0.03365 0.02840 -0.0895 0.0096 1.0000
12.500 1.6125 0.03508 0.02992 -0.0879 0.0094 1.0000
12.750 1.6207 0.03661 0.03155 -0.0863 0.0093 1.0000
13.000 1.6268 0.03839 0.03344 -0.0847 0.0091 1.0000
13.250 1.6315 0.04040 0.03556 -0.0832 0.0089 1.0000
13.500 1.6353 0.04255 0.03782 -0.0818 0.0088 1.0000
13.750 1.6384 0.04480 0.04019 -0.0806 0.0086 1.0000
14.000 1.6406 0.04723 0.04273 -0.0795 0.0085 1.0000
14.250 1.6420 0.04981 0.04542 -0.0786 0.0084 1.0000
14.500 1.6421 0.05258 0.04829 -0.0778 0.0082 1.0000
14.750 1.6415 0.05550 0.05132 -0.0772 0.0081 1.0000
15.000 1.6392 0.05873 0.05466 -0.0768 0.0080 1.0000
15.250 1.6359 0.06213 0.05817 -0.0765 0.0079 1.0000
15.500 1.6316 0.06576 0.06191 -0.0765 0.0078 1.0000
15.750 1.6256 0.06980 0.06606 -0.0768 0.0078 1.0000
16.000 1.6179 0.07426 0.07064 -0.0773 0.0077 1.0000
16.250 1.6072 0.07929 0.07580 -0.0782 0.0076 1.0000
16.500 1.5944 0.08487 0.08152 -0.0795 0.0075 1.0000
16.750 1.5797 0.09100 0.08781 -0.0813 0.0075 1.0000
17.000 1.5626 0.09779 0.09476 -0.0837 0.0075 1.0000
17.250 1.5421 0.10544 0.10257 -0.0867 0.0074 1.0000
17.500 1.5214 0.11351 0.11081 -0.0903 0.0074 1.0000
17.750 1.5019 0.12174 0.11920 -0.0944 0.0074 1.0000
18.000 1.4785 0.13113 0.12877 -0.0995 0.0073 1.0000
18.250 1.4586 0.14023 0.13802 -0.1048 0.0074 1.0000
18.500 1.4381 0.15000 0.14794 -0.1108 0.0074 1.0000
18.750 1.4146 0.16112 0.15924 -0.1179 0.0074 1.0000
19.000 1.3824 0.17552 0.17385 -0.1275 0.0075 1.0000
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Polar data table (+)
Polar graphs
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