OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF095 AIRFOIL (oaf095-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.35 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf095-il-1000000-n5.txt Download as CSV file: xf-oaf095-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9154 0.08009 0.07765 -0.0300 1.0000 0.0090
-14.000 -0.9557 0.06946 0.06691 -0.0378 1.0000 0.0089
-13.750 -1.0096 0.05690 0.05420 -0.0480 1.0000 0.0087
-13.500 -1.0486 0.03528 0.03217 -0.0787 1.0000 0.0085
-13.250 -1.0223 0.02606 0.02257 -0.0953 1.0000 0.0087
-13.000 -0.9957 0.02387 0.02024 -0.0989 1.0000 0.0090
-12.750 -0.9686 0.02229 0.01854 -0.1013 1.0000 0.0093
-12.500 -0.9410 0.02101 0.01714 -0.1032 1.0000 0.0096
-12.250 -0.9131 0.01991 0.01594 -0.1049 1.0000 0.0099
-12.000 -0.8848 0.01894 0.01487 -0.1063 1.0000 0.0102
-11.750 -0.8545 0.01807 0.01390 -0.1079 0.9912 0.0105
-11.500 -0.8232 0.01725 0.01298 -0.1096 0.9823 0.0108
-11.250 -0.7935 0.01638 0.01201 -0.1109 0.9737 0.0113
-11.000 -0.7650 0.01571 0.01127 -0.1118 0.9659 0.0119
-10.750 -0.7374 0.01515 0.01063 -0.1122 0.9581 0.0124
-10.500 -0.7096 0.01465 0.01006 -0.1126 0.9514 0.0130
-10.250 -0.6820 0.01420 0.00952 -0.1129 0.9445 0.0135
-10.000 -0.6538 0.01369 0.00893 -0.1134 0.9386 0.0141
-9.750 -0.6254 0.01319 0.00837 -0.1138 0.9322 0.0149
-9.250 -0.5683 0.01240 0.00745 -0.1146 0.9207 0.0164
-9.000 -0.5395 0.01206 0.00703 -0.1149 0.9148 0.0170
-8.750 -0.5107 0.01169 0.00659 -0.1153 0.9093 0.0179
-8.500 -0.4813 0.01133 0.00619 -0.1157 0.9034 0.0191
-8.250 -0.4523 0.01104 0.00584 -0.1161 0.8974 0.0203
-8.000 -0.4231 0.01078 0.00551 -0.1164 0.8918 0.0212
-7.750 -0.3936 0.01046 0.00515 -0.1168 0.8857 0.0226
-7.500 -0.3644 0.01019 0.00484 -0.1172 0.8797 0.0243
-7.250 -0.3348 0.00995 0.00456 -0.1175 0.8736 0.0258
-7.000 -0.3052 0.00972 0.00427 -0.1179 0.8671 0.0273
-6.750 -0.2756 0.00948 0.00400 -0.1182 0.8609 0.0295
-6.500 -0.2460 0.00927 0.00376 -0.1186 0.8541 0.0317
-6.250 -0.2164 0.00908 0.00351 -0.1189 0.8475 0.0344
-6.000 -0.1866 0.00887 0.00329 -0.1193 0.8403 0.0375
-5.500 -0.1272 0.00851 0.00287 -0.1199 0.8242 0.0459
-5.250 -0.0976 0.00837 0.00269 -0.1202 0.8155 0.0508
-5.000 -0.0677 0.00820 0.00252 -0.1206 0.8065 0.0572
-4.750 -0.0379 0.00804 0.00235 -0.1209 0.7990 0.0662
-4.500 -0.0080 0.00790 0.00221 -0.1213 0.7911 0.0745
-4.250 0.0217 0.00779 0.00208 -0.1216 0.7837 0.0829
-4.000 0.0516 0.00766 0.00196 -0.1219 0.7760 0.0926
-3.750 0.0814 0.00755 0.00185 -0.1222 0.7690 0.1023
-3.500 0.1112 0.00745 0.00176 -0.1226 0.7616 0.1127
-3.250 0.1409 0.00737 0.00167 -0.1228 0.7544 0.1237
-3.000 0.1708 0.00728 0.00160 -0.1231 0.7471 0.1370
-2.500 0.2302 0.00714 0.00149 -0.1237 0.7317 0.1616
-2.250 0.2598 0.00710 0.00144 -0.1240 0.7236 0.1728
-2.000 0.2895 0.00705 0.00141 -0.1242 0.7159 0.1828
-1.500 0.3488 0.00698 0.00135 -0.1247 0.7014 0.2047
-1.250 0.3783 0.00696 0.00134 -0.1249 0.6938 0.2169
-1.000 0.4079 0.00693 0.00133 -0.1251 0.6850 0.2301
-0.750 0.4374 0.00694 0.00133 -0.1253 0.6743 0.2421
-0.500 0.4668 0.00694 0.00133 -0.1256 0.6629 0.2568
-0.250 0.4963 0.00693 0.00135 -0.1258 0.6533 0.2716
0.000 0.5257 0.00694 0.00137 -0.1260 0.6440 0.2867
0.250 0.5551 0.00696 0.00141 -0.1262 0.6324 0.3031
0.500 0.5843 0.00701 0.00144 -0.1263 0.6165 0.3184
0.750 0.6134 0.00709 0.00149 -0.1265 0.5971 0.3310
1.000 0.6424 0.00717 0.00154 -0.1266 0.5787 0.3422
1.250 0.6714 0.00726 0.00161 -0.1268 0.5596 0.3554
1.500 0.7003 0.00739 0.00168 -0.1269 0.5384 0.3679
1.750 0.7290 0.00753 0.00177 -0.1270 0.5123 0.3796
2.000 0.7575 0.00775 0.00189 -0.1271 0.4796 0.3909
2.250 0.7858 0.00799 0.00202 -0.1272 0.4460 0.4026
2.500 0.8137 0.00834 0.00219 -0.1273 0.3948 0.4152
2.750 0.8410 0.00880 0.00243 -0.1273 0.3373 0.4302
3.000 0.8680 0.00931 0.00271 -0.1274 0.2764 0.4477
3.250 0.8952 0.00976 0.00298 -0.1274 0.2261 0.4693
3.500 0.9224 0.01016 0.00326 -0.1274 0.1862 0.4922
3.750 0.9496 0.01053 0.00353 -0.1274 0.1513 0.5143
4.000 0.9767 0.01089 0.00380 -0.1274 0.1225 0.5400
4.250 1.0039 0.01121 0.00409 -0.1273 0.0992 0.5713
4.500 1.0312 0.01147 0.00437 -0.1273 0.0820 0.6132
4.750 1.0586 0.01169 0.00468 -0.1274 0.0675 0.6849
5.000 1.0794 0.01141 0.00492 -0.1257 0.0586 1.0000
5.250 1.1063 0.01173 0.00520 -0.1256 0.0503 1.0000
5.500 1.1329 0.01207 0.00549 -0.1253 0.0432 1.0000
5.750 1.1597 0.01237 0.00576 -0.1251 0.0391 1.0000
6.000 1.1860 0.01270 0.00607 -0.1249 0.0348 1.0000
6.250 1.2125 0.01301 0.00637 -0.1246 0.0319 1.0000
6.500 1.2384 0.01338 0.00670 -0.1243 0.0283 1.0000
6.750 1.2645 0.01369 0.00703 -0.1240 0.0265 1.0000
7.000 1.2901 0.01406 0.00738 -0.1236 0.0244 1.0000
7.250 1.3155 0.01444 0.00776 -0.1232 0.0226 1.0000
7.500 1.3409 0.01479 0.00812 -0.1228 0.0214 1.0000
7.750 1.3658 0.01518 0.00852 -0.1223 0.0199 1.0000
8.000 1.3902 0.01563 0.00896 -0.1217 0.0184 1.0000
8.250 1.4147 0.01603 0.00938 -0.1212 0.0176 1.0000
8.500 1.4389 0.01644 0.00982 -0.1206 0.0169 1.0000
8.750 1.4626 0.01688 0.01029 -0.1199 0.0160 1.0000
9.000 1.4858 0.01737 0.01078 -0.1192 0.0152 1.0000
9.250 1.5080 0.01793 0.01136 -0.1183 0.0143 1.0000
9.500 1.5309 0.01839 0.01186 -0.1175 0.0139 1.0000
9.750 1.5531 0.01888 0.01238 -0.1167 0.0134 1.0000
10.000 1.5746 0.01941 0.01296 -0.1157 0.0129 1.0000
10.250 1.5955 0.01997 0.01355 -0.1147 0.0124 1.0000
10.500 1.6155 0.02057 0.01418 -0.1135 0.0120 1.0000
10.750 1.6344 0.02125 0.01489 -0.1122 0.0115 1.0000
11.000 1.6520 0.02199 0.01568 -0.1107 0.0111 1.0000
11.250 1.6698 0.02263 0.01639 -0.1092 0.0109 1.0000
11.500 1.6861 0.02331 0.01713 -0.1075 0.0107 1.0000
11.750 1.7008 0.02401 0.01789 -0.1055 0.0104 1.0000
12.000 1.7129 0.02475 0.01869 -0.1032 0.0101 1.0000
12.250 1.7235 0.02558 0.01958 -0.1007 0.0098 1.0000
12.500 1.7337 0.02652 0.02058 -0.0984 0.0095 1.0000
12.750 1.7436 0.02755 0.02167 -0.0962 0.0093 1.0000
13.000 1.7527 0.02870 0.02289 -0.0941 0.0091 1.0000
13.250 1.7605 0.03001 0.02426 -0.0920 0.0089 1.0000
13.500 1.7663 0.03155 0.02589 -0.0898 0.0086 1.0000
13.750 1.7729 0.03307 0.02750 -0.0880 0.0085 1.0000
14.000 1.7802 0.03458 0.02909 -0.0863 0.0084 1.0000
14.250 1.7865 0.03624 0.03084 -0.0847 0.0083 1.0000
14.500 1.7919 0.03802 0.03272 -0.0832 0.0081 1.0000
14.750 1.7963 0.03998 0.03477 -0.0818 0.0080 1.0000
15.000 1.7999 0.04208 0.03697 -0.0805 0.0079 1.0000
15.250 1.8026 0.04432 0.03931 -0.0794 0.0078 1.0000
15.500 1.8042 0.04674 0.04183 -0.0784 0.0076 1.0000
15.750 1.8052 0.04932 0.04451 -0.0776 0.0075 1.0000
16.000 1.8048 0.05212 0.04741 -0.0769 0.0074 1.0000
16.250 1.8032 0.05513 0.05051 -0.0764 0.0072 1.0000
16.500 1.8005 0.05838 0.05387 -0.0761 0.0071 1.0000
16.750 1.7966 0.06194 0.05753 -0.0760 0.0070 1.0000
17.000 1.7909 0.06586 0.06156 -0.0762 0.0069 1.0000
17.250 1.7837 0.07012 0.06593 -0.0767 0.0068 1.0000
17.500 1.7746 0.07484 0.07077 -0.0775 0.0068 1.0000
17.750 1.7636 0.08000 0.07606 -0.0787 0.0067 1.0000
18.000 1.7502 0.08567 0.08185 -0.0803 0.0066 1.0000
18.250 1.7346 0.09190 0.08822 -0.0823 0.0066 1.0000
18.500 1.7169 0.09870 0.09517 -0.0848 0.0065 1.0000
18.750 1.6970 0.10610 0.10272 -0.0878 0.0065 1.0000
19.000 1.6743 0.11421 0.11099 -0.0914 0.0064 1.0000
19.250 1.6509 0.12280 0.11972 -0.0956 0.0064 1.0000
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