OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF102 AIRFOIL (oaf102-il) Reynolds number: 500,000 Max Cl/Cd: 107.16 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf102-il-500000.txt Download as CSV file: xf-oaf102-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7502 0.06818 0.06561 -0.0349 1.0000 0.0159
-11.250 -0.7812 0.05789 0.05520 -0.0436 1.0000 0.0157
-11.000 -0.8013 0.04827 0.04541 -0.0547 1.0000 0.0156
-10.750 -0.7891 0.03718 0.03384 -0.0758 1.0000 0.0157
-10.500 -0.7678 0.03286 0.02912 -0.0828 1.0000 0.0159
-10.250 -0.7478 0.02740 0.02319 -0.0887 1.0000 0.0163
-10.000 -0.7217 0.02510 0.02074 -0.0913 1.0000 0.0169
-9.750 -0.6938 0.02365 0.01917 -0.0931 1.0000 0.0175
-9.500 -0.6650 0.02228 0.01764 -0.0948 1.0000 0.0182
-9.250 -0.6357 0.02097 0.01617 -0.0964 1.0000 0.0191
-9.000 -0.6058 0.01985 0.01487 -0.0979 1.0000 0.0199
-8.750 -0.5755 0.01820 0.01304 -0.0997 1.0000 0.0211
-8.500 -0.5453 0.01726 0.01206 -0.1012 1.0000 0.0225
-8.250 -0.5150 0.01659 0.01133 -0.1024 1.0000 0.0239
-8.000 -0.4848 0.01591 0.01055 -0.1034 1.0000 0.0253
-7.750 -0.4510 0.01469 0.00922 -0.1056 0.9954 0.0273
-7.500 -0.4149 0.01405 0.00854 -0.1079 0.9869 0.0296
-7.250 -0.3802 0.01365 0.00805 -0.1096 0.9776 0.0322
-7.000 -0.3469 0.01281 0.00714 -0.1112 0.9676 0.0358
-6.750 -0.3184 0.01248 0.00675 -0.1114 0.9558 0.0391
-6.500 -0.2908 0.01204 0.00621 -0.1114 0.9437 0.0434
-6.250 -0.2632 0.01169 0.00582 -0.1114 0.9322 0.0489
-6.000 -0.2349 0.01127 0.00536 -0.1116 0.9219 0.0562
-5.750 -0.2070 0.01095 0.00499 -0.1116 0.9120 0.0662
-5.500 -0.1777 0.01058 0.00464 -0.1120 0.9015 0.0813
-5.250 -0.1488 0.01030 0.00437 -0.1122 0.8920 0.1008
-5.000 -0.1198 0.01001 0.00411 -0.1125 0.8826 0.1239
-4.750 -0.0903 0.00978 0.00390 -0.1129 0.8728 0.1457
-4.500 -0.0614 0.00962 0.00376 -0.1131 0.8640 0.1688
-4.250 -0.0320 0.00949 0.00362 -0.1134 0.8545 0.1879
-4.000 -0.0027 0.00937 0.00348 -0.1137 0.8453 0.2051
-3.750 0.0264 0.00927 0.00336 -0.1138 0.8362 0.2214
-3.500 0.0560 0.00917 0.00326 -0.1142 0.8268 0.2373
-3.250 0.0853 0.00911 0.00316 -0.1144 0.8187 0.2529
-3.000 0.1150 0.00903 0.00309 -0.1147 0.8102 0.2689
-2.750 0.1444 0.00898 0.00303 -0.1150 0.8029 0.2851
-2.500 0.1741 0.00892 0.00297 -0.1153 0.7951 0.3013
-2.250 0.2036 0.00890 0.00293 -0.1156 0.7886 0.3173
-2.000 0.2334 0.00885 0.00290 -0.1159 0.7812 0.3329
-1.750 0.2627 0.00885 0.00288 -0.1161 0.7749 0.3482
-1.500 0.2925 0.00882 0.00287 -0.1165 0.7677 0.3631
-1.250 0.3219 0.00882 0.00286 -0.1167 0.7613 0.3775
-1.000 0.3516 0.00881 0.00288 -0.1170 0.7549 0.3916
-0.750 0.3812 0.00881 0.00289 -0.1173 0.7485 0.4052
-0.500 0.4106 0.00883 0.00291 -0.1175 0.7424 0.4188
-0.250 0.4402 0.00882 0.00293 -0.1178 0.7352 0.4329
0.000 0.4694 0.00887 0.00296 -0.1180 0.7292 0.4467
0.250 0.4991 0.00886 0.00300 -0.1183 0.7224 0.4596
0.500 0.5285 0.00887 0.00304 -0.1185 0.7164 0.4720
0.750 0.5580 0.00889 0.00309 -0.1188 0.7103 0.4848
1.000 0.5876 0.00889 0.00315 -0.1191 0.7038 0.4982
1.250 0.6168 0.00894 0.00321 -0.1193 0.6981 0.5125
1.500 0.6464 0.00892 0.00329 -0.1196 0.6913 0.5287
1.750 0.6757 0.00895 0.00336 -0.1198 0.6852 0.5469
2.000 0.7053 0.00896 0.00347 -0.1201 0.6787 0.5675
2.250 0.7347 0.00894 0.00356 -0.1204 0.6719 0.5922
2.750 0.7924 0.00872 0.00365 -0.1206 0.6415 0.6967
3.000 0.8106 0.00806 0.00351 -0.1179 0.6226 1.0000
3.250 0.8397 0.00815 0.00355 -0.1181 0.6027 1.0000
3.500 0.8687 0.00827 0.00364 -0.1182 0.5849 1.0000
3.750 0.8974 0.00844 0.00375 -0.1184 0.5636 1.0000
4.000 0.9259 0.00864 0.00387 -0.1185 0.5353 1.0000
4.250 0.9539 0.00897 0.00404 -0.1185 0.4927 1.0000
4.500 0.9807 0.00956 0.00433 -0.1185 0.4274 1.0000
4.750 1.0038 0.01106 0.00502 -0.1185 0.2705 1.0000
5.000 1.0250 0.01289 0.00599 -0.1183 0.1181 1.0000
5.250 1.0497 0.01382 0.00662 -0.1181 0.0707 1.0000
5.500 1.0754 0.01447 0.00719 -0.1179 0.0546 1.0000
5.750 1.1006 0.01517 0.00784 -0.1176 0.0451 1.0000
6.000 1.1270 0.01559 0.00830 -0.1174 0.0410 1.0000
6.250 1.1505 0.01647 0.00917 -0.1168 0.0359 1.0000
6.500 1.1761 0.01693 0.00968 -0.1164 0.0336 1.0000
6.750 1.2009 0.01747 0.01024 -0.1160 0.0310 1.0000
7.000 1.2217 0.01856 0.01134 -0.1150 0.0284 1.0000
7.250 1.2444 0.01931 0.01216 -0.1142 0.0272 1.0000
7.500 1.2674 0.01997 0.01289 -0.1135 0.0257 1.0000
7.750 1.2899 0.02064 0.01358 -0.1127 0.0243 1.0000
8.000 1.3106 0.02147 0.01442 -0.1118 0.0229 1.0000
8.250 1.3246 0.02321 0.01623 -0.1097 0.0217 1.0000
8.500 1.3457 0.02396 0.01706 -0.1087 0.0211 1.0000
8.750 1.3651 0.02489 0.01808 -0.1074 0.0203 1.0000
9.000 1.3836 0.02589 0.01916 -0.1060 0.0196 1.0000
9.250 1.4014 0.02691 0.02024 -0.1046 0.0189 1.0000
9.500 1.4185 0.02789 0.02126 -0.1031 0.0183 1.0000
9.750 1.4335 0.02911 0.02251 -0.1014 0.0176 1.0000
10.000 1.4462 0.03167 0.02520 -0.0995 0.0168 1.0000
10.250 1.4609 0.03266 0.02635 -0.0976 0.0165 1.0000
10.500 1.4742 0.03404 0.02788 -0.0956 0.0161 1.0000
10.750 1.4858 0.03560 0.02960 -0.0935 0.0156 1.0000
11.000 1.4939 0.03727 0.03143 -0.0909 0.0153 1.0000
11.250 1.5004 0.03905 0.03337 -0.0883 0.0150 1.0000
11.500 1.5057 0.04093 0.03540 -0.0858 0.0147 1.0000
11.750 1.5099 0.04288 0.03749 -0.0834 0.0144 1.0000
12.000 1.5121 0.04502 0.03979 -0.0812 0.0142 1.0000
12.250 1.5130 0.04732 0.04226 -0.0791 0.0140 1.0000
12.500 1.5125 0.04975 0.04483 -0.0772 0.0138 1.0000
12.750 1.5116 0.05228 0.04747 -0.0756 0.0136 1.0000
13.000 1.5072 0.05545 0.05078 -0.0741 0.0133 1.0000
13.250 1.4953 0.05982 0.05538 -0.0725 0.0132 1.0000
13.500 1.4754 0.06536 0.06118 -0.0714 0.0130 1.0000
14.000 1.4298 0.07744 0.07379 -0.0715 0.0129 1.0000
14.250 1.4121 0.08303 0.07960 -0.0727 0.0129 1.0000
14.500 1.3911 0.08956 0.08634 -0.0746 0.0129 1.0000
14.750 1.3678 0.09698 0.09397 -0.0774 0.0129 1.0000
15.000 1.3431 0.10539 0.10258 -0.0813 0.0129 1.0000
15.250 1.3180 0.11464 0.11202 -0.0862 0.0130 1.0000
15.500 1.2995 0.12332 0.12087 -0.0917 0.0130 1.0000
15.750 1.2818 0.13273 0.13044 -0.0980 0.0131 1.0000
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