OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: OAF095 AIRFOIL (oaf095-il) Reynolds number: 500,000 Max Cl/Cd: 93.21 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf095-il-500000-n5.txt Download as CSV file: xf-oaf095-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: OAF095 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6892 0.11434 0.11184 -0.0100 1.0000 0.0130
-13.500 -0.7796 0.09096 0.08821 -0.0232 1.0000 0.0127
-13.250 -0.8083 0.08126 0.07842 -0.0295 1.0000 0.0127
-13.000 -0.8351 0.07237 0.06943 -0.0358 1.0000 0.0126
-12.750 -0.8616 0.06384 0.06081 -0.0424 1.0000 0.0126
-12.500 -0.8893 0.05517 0.05203 -0.0498 1.0000 0.0125
-12.250 -0.9023 0.04421 0.04088 -0.0648 1.0000 0.0125
-12.000 -0.8878 0.03323 0.02958 -0.0836 1.0000 0.0127
-11.750 -0.8582 0.02785 0.02387 -0.0940 1.0000 0.0131
-11.500 -0.8308 0.02560 0.02139 -0.0978 1.0000 0.0136
-11.250 -0.8030 0.02352 0.01914 -0.1012 1.0000 0.0141
-11.000 -0.7750 0.02207 0.01758 -0.1035 1.0000 0.0147
-10.750 -0.7467 0.02091 0.01630 -0.1052 1.0000 0.0152
-10.500 -0.7184 0.01987 0.01514 -0.1067 1.0000 0.0159
-10.250 -0.6863 0.01888 0.01401 -0.1088 0.9935 0.0166
-10.000 -0.6536 0.01802 0.01299 -0.1107 0.9869 0.0172
-9.750 -0.6207 0.01700 0.01189 -0.1129 0.9813 0.0181
-9.500 -0.5891 0.01634 0.01115 -0.1144 0.9749 0.0192
-9.250 -0.5578 0.01574 0.01045 -0.1156 0.9689 0.0203
-9.000 -0.5281 0.01521 0.00980 -0.1164 0.9619 0.0212
-8.750 -0.4986 0.01454 0.00905 -0.1173 0.9555 0.0224
-8.500 -0.4700 0.01404 0.00849 -0.1178 0.9485 0.0236
-8.250 -0.4418 0.01364 0.00800 -0.1180 0.9421 0.0251
-8.000 -0.4132 0.01327 0.00753 -0.1183 0.9356 0.0263
-7.750 -0.3846 0.01276 0.00696 -0.1187 0.9292 0.0281
-7.500 -0.3560 0.01238 0.00653 -0.1190 0.9231 0.0299
-7.250 -0.3273 0.01207 0.00613 -0.1193 0.9166 0.0318
-6.750 -0.2693 0.01137 0.00533 -0.1199 0.9043 0.0369
-6.500 -0.2405 0.01112 0.00499 -0.1200 0.8979 0.0394
-6.250 -0.2112 0.01079 0.00464 -0.1204 0.8919 0.0435
-6.000 -0.1819 0.01055 0.00435 -0.1207 0.8851 0.0475
-5.750 -0.1529 0.01028 0.00405 -0.1209 0.8789 0.0529
-5.500 -0.1232 0.01005 0.00379 -0.1213 0.8720 0.0592
-5.250 -0.0940 0.00983 0.00355 -0.1215 0.8652 0.0675
-5.000 -0.0644 0.00961 0.00334 -0.1218 0.8583 0.0764
-4.750 -0.0350 0.00942 0.00313 -0.1221 0.8509 0.0859
-4.500 -0.0057 0.00927 0.00295 -0.1223 0.8433 0.0952
-4.250 0.0237 0.00911 0.00278 -0.1225 0.8348 0.1064
-4.000 0.0532 0.00895 0.00263 -0.1228 0.8268 0.1181
-3.750 0.0827 0.00882 0.00250 -0.1230 0.8191 0.1307
-3.500 0.1123 0.00870 0.00239 -0.1233 0.8117 0.1441
-3.250 0.1417 0.00861 0.00228 -0.1235 0.8039 0.1567
-3.000 0.1712 0.00852 0.00219 -0.1237 0.7963 0.1688
-2.750 0.2007 0.00844 0.00210 -0.1239 0.7886 0.1810
-2.500 0.2302 0.00836 0.00203 -0.1241 0.7814 0.1939
-2.250 0.2597 0.00829 0.00197 -0.1244 0.7737 0.2066
-2.000 0.2892 0.00824 0.00192 -0.1246 0.7665 0.2182
-1.750 0.3187 0.00819 0.00188 -0.1248 0.7584 0.2320
-1.500 0.3482 0.00815 0.00185 -0.1250 0.7506 0.2458
-1.250 0.3775 0.00813 0.00183 -0.1251 0.7422 0.2592
-1.000 0.4070 0.00810 0.00183 -0.1253 0.7347 0.2750
-0.750 0.4364 0.00808 0.00183 -0.1255 0.7269 0.2902
-0.500 0.4658 0.00807 0.00185 -0.1257 0.7191 0.3061
-0.250 0.4950 0.00807 0.00187 -0.1258 0.7101 0.3226
0.000 0.5243 0.00808 0.00189 -0.1260 0.6994 0.3383
0.250 0.5534 0.00810 0.00193 -0.1261 0.6889 0.3523
0.500 0.5825 0.00813 0.00197 -0.1262 0.6791 0.3657
0.750 0.6117 0.00815 0.00202 -0.1263 0.6692 0.3801
1.000 0.6407 0.00820 0.00208 -0.1264 0.6572 0.3934
1.250 0.6695 0.00827 0.00213 -0.1265 0.6405 0.4063
1.500 0.6982 0.00836 0.00220 -0.1265 0.6218 0.4197
1.750 0.7269 0.00845 0.00228 -0.1266 0.6042 0.4342
2.250 0.7839 0.00868 0.00248 -0.1266 0.5616 0.4695
2.500 0.8121 0.00885 0.00261 -0.1267 0.5328 0.4922
2.750 0.8401 0.00905 0.00277 -0.1267 0.5007 0.5181
3.000 0.8678 0.00931 0.00296 -0.1267 0.4639 0.5457
3.250 0.8952 0.00962 0.00318 -0.1267 0.4191 0.5782
3.500 0.9213 0.01015 0.00351 -0.1266 0.3508 0.6228
3.750 0.9469 0.01069 0.00393 -0.1265 0.2821 0.6992
4.000 0.9638 0.01071 0.00420 -0.1241 0.2321 1.0000
4.250 0.9895 0.01133 0.00458 -0.1239 0.1852 1.0000
4.500 1.0153 0.01191 0.00496 -0.1237 0.1468 1.0000
4.750 1.0410 0.01245 0.00533 -0.1234 0.1167 1.0000
5.000 1.0669 0.01294 0.00569 -0.1232 0.0940 1.0000
5.250 1.0927 0.01341 0.00607 -0.1229 0.0771 1.0000
5.500 1.1184 0.01387 0.00645 -0.1225 0.0645 1.0000
5.750 1.1442 0.01429 0.00683 -0.1222 0.0556 1.0000
6.000 1.1698 0.01470 0.00723 -0.1218 0.0488 1.0000
6.250 1.1949 0.01517 0.00765 -0.1214 0.0428 1.0000
6.500 1.2202 0.01558 0.00807 -0.1210 0.0387 1.0000
6.750 1.2448 0.01608 0.00854 -0.1205 0.0350 1.0000
7.000 1.2697 0.01650 0.00900 -0.1200 0.0325 1.0000
7.250 1.2937 0.01700 0.00950 -0.1194 0.0298 1.0000
7.500 1.3174 0.01752 0.01004 -0.1187 0.0276 1.0000
7.750 1.3412 0.01800 0.01056 -0.1181 0.0259 1.0000
8.000 1.3642 0.01855 0.01113 -0.1173 0.0244 1.0000
8.250 1.3859 0.01923 0.01181 -0.1164 0.0228 1.0000
8.500 1.4084 0.01976 0.01241 -0.1155 0.0218 1.0000
8.750 1.4303 0.02033 0.01303 -0.1146 0.0207 1.0000
9.000 1.4514 0.02095 0.01369 -0.1136 0.0196 1.0000
9.250 1.4711 0.02167 0.01443 -0.1124 0.0187 1.0000
9.500 1.4895 0.02249 0.01530 -0.1111 0.0180 1.0000
9.750 1.5084 0.02319 0.01608 -0.1097 0.0174 1.0000
10.000 1.5262 0.02395 0.01691 -0.1083 0.0168 1.0000
10.250 1.5429 0.02472 0.01776 -0.1067 0.0162 1.0000
10.500 1.5584 0.02551 0.01861 -0.1049 0.0156 1.0000
10.750 1.5717 0.02637 0.01952 -0.1028 0.0151 1.0000
11.000 1.5799 0.02743 0.02064 -0.1001 0.0146 1.0000
11.250 1.5881 0.02860 0.02189 -0.0975 0.0142 1.0000
11.500 1.5980 0.02972 0.02311 -0.0953 0.0139 1.0000
11.750 1.6071 0.03095 0.02445 -0.0932 0.0136 1.0000
12.000 1.6156 0.03228 0.02589 -0.0912 0.0133 1.0000
12.250 1.6235 0.03372 0.02743 -0.0893 0.0130 1.0000
12.500 1.6308 0.03526 0.02907 -0.0875 0.0127 1.0000
12.750 1.6374 0.03691 0.03081 -0.0858 0.0124 1.0000
13.000 1.6435 0.03866 0.03266 -0.0843 0.0121 1.0000
13.250 1.6486 0.04056 0.03466 -0.0828 0.0119 1.0000
13.500 1.6521 0.04269 0.03688 -0.0815 0.0116 1.0000
13.750 1.6529 0.04517 0.03946 -0.0802 0.0114 1.0000
14.000 1.6500 0.04814 0.04254 -0.0791 0.0112 1.0000
14.250 1.6515 0.05072 0.04526 -0.0782 0.0110 1.0000
14.500 1.6522 0.05347 0.04816 -0.0775 0.0109 1.0000
14.750 1.6508 0.05655 0.05137 -0.0770 0.0107 1.0000
15.000 1.6481 0.05988 0.05485 -0.0767 0.0105 1.0000
15.250 1.6439 0.06351 0.05862 -0.0766 0.0104 1.0000
15.500 1.6382 0.06746 0.06272 -0.0768 0.0102 1.0000
15.750 1.6318 0.07170 0.06710 -0.0773 0.0101 1.0000
16.000 1.6241 0.07631 0.07186 -0.0782 0.0100 1.0000
16.250 1.6154 0.08124 0.07693 -0.0794 0.0099 1.0000
16.500 1.6052 0.08655 0.08239 -0.0809 0.0098 1.0000
16.750 1.5937 0.09228 0.08827 -0.0828 0.0097 1.0000
17.000 1.5810 0.09842 0.09456 -0.0851 0.0096 1.0000
17.250 1.5670 0.10496 0.10125 -0.0878 0.0096 1.0000
17.500 1.5516 0.11195 0.10840 -0.0910 0.0095 1.0000
17.750 1.5352 0.11942 0.11602 -0.0946 0.0095 1.0000
18.000 1.5180 0.12732 0.12407 -0.0987 0.0094 1.0000
18.250 1.4996 0.13566 0.13257 -0.1033 0.0094 1.0000
18.500 1.4804 0.14447 0.14153 -0.1085 0.0094 1.0000
18.750 1.4607 0.15374 0.15096 -0.1141 0.0093 1.0000
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