OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF102 AIRFOIL (oaf102-il) Reynolds number: 200,000 Max Cl/Cd: 77.44 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf102-il-200000-n5.txt Download as CSV file: xf-oaf102-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7015 0.06522 0.06152 -0.0398 1.0000 0.0182
-10.500 -0.7414 0.05124 0.04729 -0.0546 1.0000 0.0176
-10.250 -0.7334 0.04048 0.03607 -0.0737 1.0000 0.0179
-10.000 -0.7136 0.03565 0.03082 -0.0813 1.0000 0.0186
-9.750 -0.6906 0.03201 0.02673 -0.0860 1.0000 0.0193
-9.500 -0.6650 0.02916 0.02348 -0.0893 1.0000 0.0201
-9.250 -0.6386 0.02688 0.02096 -0.0917 1.0000 0.0208
-9.000 -0.6110 0.02535 0.01932 -0.0936 1.0000 0.0217
-8.750 -0.5827 0.02411 0.01795 -0.0952 1.0000 0.0231
-8.500 -0.5540 0.02287 0.01649 -0.0967 1.0000 0.0248
-8.250 -0.5251 0.02156 0.01499 -0.0981 1.0000 0.0264
-8.000 -0.4965 0.02044 0.01381 -0.0995 1.0000 0.0279
-7.750 -0.4654 0.01952 0.01279 -0.1011 0.9950 0.0300
-7.500 -0.4299 0.01870 0.01177 -0.1034 0.9853 0.0328
-7.250 -0.3945 0.01767 0.01069 -0.1059 0.9767 0.0360
-7.000 -0.3594 0.01695 0.00983 -0.1080 0.9680 0.0395
-6.750 -0.3253 0.01620 0.00901 -0.1098 0.9586 0.0442
-6.500 -0.2930 0.01565 0.00834 -0.1111 0.9486 0.0495
-6.250 -0.2613 0.01507 0.00771 -0.1123 0.9388 0.0564
-6.000 -0.2311 0.01461 0.00718 -0.1130 0.9285 0.0650
-5.750 -0.2014 0.01418 0.00670 -0.1135 0.9181 0.0761
-5.500 -0.1722 0.01379 0.00630 -0.1140 0.9084 0.0911
-5.250 -0.1434 0.01344 0.00595 -0.1143 0.8986 0.1091
-5.000 -0.1144 0.01315 0.00563 -0.1146 0.8888 0.1289
-4.750 -0.0858 0.01289 0.00539 -0.1148 0.8799 0.1500
-4.500 -0.0569 0.01270 0.00518 -0.1151 0.8704 0.1715
-4.250 -0.0281 0.01253 0.00499 -0.1152 0.8617 0.1907
-4.000 0.0006 0.01238 0.00481 -0.1154 0.8530 0.2090
-3.750 0.0297 0.01225 0.00466 -0.1156 0.8444 0.2267
-3.500 0.0583 0.01215 0.00452 -0.1157 0.8364 0.2437
-3.250 0.0876 0.01205 0.00440 -0.1159 0.8278 0.2602
-3.000 0.1163 0.01198 0.00428 -0.1160 0.8204 0.2761
-2.750 0.1458 0.01190 0.00420 -0.1163 0.8118 0.2914
-2.500 0.1746 0.01185 0.00410 -0.1163 0.8041 0.3066
-2.000 0.2328 0.01177 0.00399 -0.1167 0.7881 0.3366
-1.750 0.2622 0.01173 0.00395 -0.1169 0.7804 0.3517
-1.500 0.2912 0.01172 0.00392 -0.1170 0.7741 0.3664
-1.250 0.3207 0.01170 0.00393 -0.1173 0.7666 0.3813
-1.000 0.3498 0.01171 0.00392 -0.1175 0.7604 0.3960
-0.750 0.3793 0.01170 0.00395 -0.1177 0.7538 0.4102
-0.500 0.4085 0.01170 0.00396 -0.1179 0.7474 0.4230
-0.250 0.4377 0.01172 0.00399 -0.1181 0.7412 0.4352
0.000 0.4670 0.01173 0.00403 -0.1183 0.7344 0.4476
0.250 0.4960 0.01176 0.00406 -0.1184 0.7290 0.4611
0.500 0.5254 0.01177 0.00415 -0.1187 0.7218 0.4751
0.750 0.5543 0.01180 0.00420 -0.1188 0.7154 0.4889
1.000 0.5835 0.01182 0.00429 -0.1190 0.7083 0.5029
1.250 0.6125 0.01185 0.00439 -0.1192 0.7016 0.5192
1.500 0.6415 0.01187 0.00450 -0.1193 0.6952 0.5383
1.750 0.6706 0.01188 0.00463 -0.1195 0.6882 0.5604
2.000 0.6994 0.01190 0.00476 -0.1196 0.6821 0.5843
2.250 0.7284 0.01190 0.00493 -0.1198 0.6747 0.6128
2.500 0.7566 0.01188 0.00506 -0.1197 0.6686 0.6506
2.750 0.7841 0.01178 0.00525 -0.1195 0.6608 0.7149
3.000 0.8014 0.01126 0.00515 -0.1165 0.6543 1.0000
3.250 0.8304 0.01137 0.00527 -0.1166 0.6413 1.0000
3.500 0.8582 0.01145 0.00528 -0.1164 0.6156 1.0000
3.750 0.8853 0.01158 0.00527 -0.1160 0.5789 1.0000
4.000 0.9125 0.01180 0.00536 -0.1157 0.5378 1.0000
4.250 0.9394 0.01213 0.00552 -0.1155 0.4942 1.0000
4.500 0.9650 0.01269 0.00579 -0.1152 0.4322 1.0000
4.750 0.9871 0.01385 0.00635 -0.1147 0.3143 1.0000
5.000 1.0058 0.01571 0.00736 -0.1141 0.1678 1.0000
5.250 1.0277 0.01694 0.00820 -0.1137 0.1007 1.0000
5.500 1.0514 0.01780 0.00890 -0.1133 0.0733 1.0000
5.750 1.0755 0.01855 0.00960 -0.1129 0.0597 1.0000
6.000 1.0994 0.01925 0.01032 -0.1124 0.0512 1.0000
6.250 1.1222 0.02008 0.01111 -0.1118 0.0448 1.0000
6.500 1.1456 0.02077 0.01189 -0.1111 0.0408 1.0000
6.750 1.1675 0.02161 0.01276 -0.1104 0.0373 1.0000
7.000 1.1883 0.02253 0.01372 -0.1094 0.0344 1.0000
7.250 1.2096 0.02334 0.01461 -0.1085 0.0318 1.0000
7.500 1.2294 0.02426 0.01558 -0.1074 0.0299 1.0000
7.750 1.2463 0.02549 0.01683 -0.1060 0.0283 1.0000
8.000 1.2645 0.02653 0.01797 -0.1046 0.0269 1.0000
8.250 1.2828 0.02752 0.01906 -0.1033 0.0254 1.0000
8.500 1.3001 0.02854 0.02015 -0.1019 0.0240 1.0000
8.750 1.3160 0.02967 0.02133 -0.1003 0.0230 1.0000
9.000 1.3295 0.03104 0.02275 -0.0984 0.0222 1.0000
9.250 1.3431 0.03257 0.02437 -0.0965 0.0215 1.0000
9.500 1.3580 0.03392 0.02588 -0.0948 0.0208 1.0000
9.750 1.3719 0.03528 0.02740 -0.0930 0.0199 1.0000
10.000 1.3831 0.03660 0.02885 -0.0908 0.0190 1.0000
10.250 1.3934 0.03795 0.03031 -0.0887 0.0183 1.0000
10.500 1.4030 0.03942 0.03186 -0.0868 0.0178 1.0000
10.750 1.4122 0.04113 0.03368 -0.0849 0.0174 1.0000
11.000 1.4206 0.04327 0.03592 -0.0831 0.0169 1.0000
11.250 1.4281 0.04548 0.03837 -0.0811 0.0166 1.0000
11.500 1.4333 0.04793 0.04111 -0.0792 0.0163 1.0000
11.750 1.4358 0.05068 0.04414 -0.0772 0.0159 1.0000
12.000 1.4351 0.05370 0.04745 -0.0753 0.0156 1.0000
12.250 1.4319 0.05694 0.05097 -0.0736 0.0153 1.0000
12.500 1.4265 0.06040 0.05469 -0.0722 0.0150 1.0000
12.750 1.4197 0.06403 0.05857 -0.0712 0.0147 1.0000
13.000 1.4114 0.06791 0.06267 -0.0706 0.0145 1.0000
13.250 1.4015 0.07211 0.06709 -0.0705 0.0142 1.0000
13.500 1.3901 0.07668 0.07187 -0.0707 0.0141 1.0000
13.750 1.3771 0.08163 0.07703 -0.0715 0.0139 1.0000
14.000 1.3629 0.08703 0.08262 -0.0729 0.0138 1.0000
14.250 1.3448 0.09340 0.08922 -0.0750 0.0137 1.0000
14.500 1.3239 0.10077 0.09682 -0.0781 0.0137 1.0000
14.750 1.2967 0.11023 0.10655 -0.0831 0.0137 1.0000
15.000 1.2402 0.12856 0.12533 -0.0948 0.0141 1.0000
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