OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF095 AIRFOIL (oaf095-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.18 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf095-il-1000000.txt Download as CSV file: xf-oaf095-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7967 0.10559 0.10364 -0.0135 1.0000 0.0121
-14.250 -0.8402 0.09276 0.09066 -0.0211 1.0000 0.0120
-14.000 -0.8687 0.08331 0.08110 -0.0272 1.0000 0.0120
-13.750 -0.8965 0.07433 0.07202 -0.0334 1.0000 0.0119
-13.500 -0.9240 0.06585 0.06343 -0.0397 1.0000 0.0119
-13.250 -0.9552 0.05690 0.05438 -0.0471 1.0000 0.0118
-13.000 -0.9781 0.04603 0.04335 -0.0604 1.0000 0.0117
-12.750 -0.9717 0.03376 0.03080 -0.0808 1.0000 0.0118
-12.500 -0.9416 0.02689 0.02364 -0.0939 1.0000 0.0121
-12.250 -0.9142 0.02465 0.02125 -0.0979 1.0000 0.0125
-12.000 -0.8864 0.02296 0.01943 -0.1006 1.0000 0.0129
-11.750 -0.8583 0.02160 0.01793 -0.1028 1.0000 0.0133
-11.500 -0.8299 0.02054 0.01675 -0.1044 1.0000 0.0136
-11.250 -0.8009 0.01873 0.01476 -0.1070 1.0000 0.0142
-11.000 -0.7717 0.01754 0.01349 -0.1088 1.0000 0.0148
-10.750 -0.7425 0.01681 0.01270 -0.1100 1.0000 0.0154
-10.500 -0.7132 0.01617 0.01199 -0.1110 1.0000 0.0161
-10.250 -0.6842 0.01563 0.01138 -0.1118 1.0000 0.0168
-10.000 -0.6530 0.01522 0.01089 -0.1129 0.9971 0.0172
-9.750 -0.6185 0.01396 0.00954 -0.1155 0.9930 0.0186
-9.500 -0.5856 0.01346 0.00899 -0.1170 0.9875 0.0195
-9.250 -0.5531 0.01302 0.00849 -0.1183 0.9821 0.0205
-9.000 -0.5236 0.01269 0.00808 -0.1188 0.9748 0.0212
-8.750 -0.4946 0.01197 0.00727 -0.1194 0.9680 0.0226
-8.500 -0.4672 0.01161 0.00688 -0.1195 0.9604 0.0240
-8.250 -0.4400 0.01136 0.00657 -0.1194 0.9538 0.0253
-8.000 -0.4124 0.01114 0.00629 -0.1193 0.9470 0.0263
-7.750 -0.3842 0.01060 0.00567 -0.1195 0.9411 0.0284
-7.500 -0.3552 0.01030 0.00534 -0.1198 0.9349 0.0302
-7.250 -0.3272 0.01010 0.00509 -0.1198 0.9287 0.0319
-7.000 -0.2979 0.00971 0.00464 -0.1201 0.9230 0.0344
-6.750 -0.2686 0.00943 0.00433 -0.1204 0.9167 0.0372
-6.250 -0.2102 0.00891 0.00375 -0.1209 0.9047 0.0442
-6.000 -0.1812 0.00874 0.00352 -0.1211 0.8984 0.0477
-5.750 -0.1516 0.00846 0.00325 -0.1214 0.8921 0.0547
-5.500 -0.1220 0.00824 0.00302 -0.1217 0.8848 0.0624
-5.250 -0.0928 0.00806 0.00283 -0.1219 0.8780 0.0713
-5.000 -0.0630 0.00788 0.00266 -0.1222 0.8707 0.0812
-4.750 -0.0337 0.00771 0.00249 -0.1224 0.8641 0.0930
-4.500 -0.0038 0.00754 0.00234 -0.1228 0.8572 0.1041
-4.250 0.0258 0.00741 0.00221 -0.1230 0.8503 0.1158
-4.000 0.0555 0.00727 0.00210 -0.1233 0.8437 0.1288
-3.750 0.0851 0.00716 0.00200 -0.1236 0.8365 0.1426
-3.500 0.1147 0.00707 0.00191 -0.1238 0.8298 0.1555
-3.250 0.1443 0.00700 0.00183 -0.1240 0.8223 0.1664
-3.000 0.1738 0.00692 0.00176 -0.1242 0.8154 0.1790
-2.750 0.2036 0.00683 0.00170 -0.1245 0.8076 0.1916
-2.500 0.2331 0.00678 0.00164 -0.1247 0.8001 0.2041
-2.250 0.2628 0.00671 0.00159 -0.1249 0.7919 0.2182
-2.000 0.2923 0.00667 0.00155 -0.1251 0.7844 0.2325
-1.750 0.3220 0.00661 0.00152 -0.1254 0.7764 0.2479
-1.500 0.3515 0.00658 0.00150 -0.1256 0.7689 0.2627
-1.250 0.3811 0.00654 0.00149 -0.1258 0.7606 0.2790
-1.000 0.4105 0.00652 0.00148 -0.1260 0.7521 0.2949
-0.750 0.4399 0.00651 0.00148 -0.1262 0.7420 0.3093
-0.500 0.4694 0.00650 0.00148 -0.1263 0.7322 0.3249
-0.250 0.4987 0.00652 0.00150 -0.1265 0.7232 0.3400
0.000 0.5282 0.00651 0.00152 -0.1267 0.7138 0.3554
0.250 0.5575 0.00652 0.00155 -0.1268 0.7039 0.3714
0.500 0.5867 0.00656 0.00158 -0.1270 0.6915 0.3869
0.750 0.6158 0.00660 0.00161 -0.1271 0.6774 0.4013
1.000 0.6450 0.00663 0.00165 -0.1272 0.6641 0.4157
1.250 0.6742 0.00667 0.00170 -0.1273 0.6507 0.4315
1.500 0.7033 0.00672 0.00175 -0.1275 0.6364 0.4475
1.750 0.7324 0.00679 0.00182 -0.1276 0.6202 0.4638
2.000 0.7613 0.00688 0.00189 -0.1277 0.6014 0.4815
2.250 0.7902 0.00696 0.00198 -0.1278 0.5823 0.5014
2.500 0.8190 0.00706 0.00207 -0.1279 0.5604 0.5242
2.750 0.8478 0.00718 0.00219 -0.1281 0.5377 0.5539
3.000 0.8764 0.00731 0.00233 -0.1282 0.5094 0.5960
3.250 0.9051 0.00742 0.00252 -0.1285 0.4777 0.6742
3.500 0.9261 0.00706 0.00267 -0.1268 0.4440 1.0000
3.750 0.9531 0.00759 0.00290 -0.1268 0.3801 1.0000
4.000 0.9792 0.00830 0.00324 -0.1267 0.3057 1.0000
4.250 1.0050 0.00902 0.00361 -0.1266 0.2368 1.0000
4.500 1.0310 0.00964 0.00396 -0.1264 0.1854 1.0000
4.750 1.0569 0.01022 0.00431 -0.1262 0.1424 1.0000
5.000 1.0831 0.01073 0.00465 -0.1260 0.1105 1.0000
5.250 1.1092 0.01122 0.00499 -0.1258 0.0860 1.0000
5.500 1.1354 0.01166 0.00532 -0.1255 0.0692 1.0000
5.750 1.1616 0.01206 0.00566 -0.1253 0.0576 1.0000
6.000 1.1878 0.01245 0.00600 -0.1250 0.0495 1.0000
6.250 1.2136 0.01287 0.00638 -0.1246 0.0426 1.0000
6.500 1.2395 0.01324 0.00673 -0.1243 0.0383 1.0000
6.750 1.2650 0.01368 0.00716 -0.1239 0.0344 1.0000
7.000 1.2907 0.01404 0.00752 -0.1235 0.0318 1.0000
7.250 1.3147 0.01464 0.00810 -0.1228 0.0284 1.0000
7.500 1.3404 0.01495 0.00844 -0.1224 0.0271 1.0000
7.750 1.3652 0.01535 0.00885 -0.1220 0.0254 1.0000
8.000 1.3886 0.01594 0.00943 -0.1212 0.0234 1.0000
8.250 1.4120 0.01648 0.01002 -0.1205 0.0223 1.0000
8.500 1.4360 0.01691 0.01048 -0.1199 0.0214 1.0000
8.750 1.4594 0.01738 0.01099 -0.1191 0.0204 1.0000
9.000 1.4818 0.01794 0.01155 -0.1183 0.0194 1.0000
9.250 1.5004 0.01892 0.01258 -0.1169 0.0181 1.0000
9.500 1.5231 0.01936 0.01306 -0.1161 0.0177 1.0000
9.750 1.5446 0.01991 0.01366 -0.1151 0.0171 1.0000
10.000 1.5652 0.02050 0.01430 -0.1140 0.0165 1.0000
10.250 1.5851 0.02112 0.01496 -0.1128 0.0160 1.0000
10.500 1.6036 0.02182 0.01569 -0.1114 0.0154 1.0000
10.750 1.6182 0.02282 0.01674 -0.1095 0.0148 1.0000
11.000 1.6265 0.02421 0.01823 -0.1066 0.0143 1.0000
11.250 1.6426 0.02482 0.01890 -0.1048 0.0140 1.0000
11.500 1.6547 0.02557 0.01973 -0.1025 0.0138 1.0000
11.750 1.6660 0.02638 0.02061 -0.1001 0.0134 1.0000
12.000 1.6764 0.02733 0.02163 -0.0978 0.0131 1.0000
12.250 1.6859 0.02840 0.02277 -0.0956 0.0128 1.0000
12.500 1.6951 0.02957 0.02401 -0.0935 0.0125 1.0000
12.750 1.7038 0.03082 0.02532 -0.0915 0.0122 1.0000
13.000 1.7108 0.03229 0.02685 -0.0895 0.0120 1.0000
13.250 1.7144 0.03410 0.02875 -0.0874 0.0117 1.0000
13.500 1.7122 0.03655 0.03132 -0.0851 0.0114 1.0000
13.750 1.7024 0.03988 0.03480 -0.0826 0.0112 1.0000
14.000 1.7087 0.04171 0.03673 -0.0814 0.0111 1.0000
14.250 1.7129 0.04381 0.03893 -0.0803 0.0110 1.0000
14.500 1.7159 0.04607 0.04130 -0.0792 0.0108 1.0000
14.750 1.7179 0.04855 0.04388 -0.0783 0.0107 1.0000
15.000 1.7185 0.05125 0.04670 -0.0776 0.0105 1.0000
15.250 1.7184 0.05409 0.04965 -0.0770 0.0103 1.0000
15.500 1.7164 0.05725 0.05292 -0.0766 0.0102 1.0000
15.750 1.7141 0.06057 0.05636 -0.0765 0.0100 1.0000
16.000 1.7100 0.06427 0.06016 -0.0766 0.0099 1.0000
16.250 1.7053 0.06815 0.06416 -0.0769 0.0098 1.0000
16.500 1.6989 0.07245 0.06857 -0.0776 0.0096 1.0000
16.750 1.6909 0.07715 0.07338 -0.0785 0.0095 1.0000
17.000 1.6815 0.08221 0.07856 -0.0798 0.0095 1.0000
17.250 1.6703 0.08769 0.08416 -0.0814 0.0094 1.0000
17.500 1.6576 0.09360 0.09019 -0.0834 0.0093 1.0000
17.750 1.6433 0.09996 0.09669 -0.0858 0.0093 1.0000
18.000 1.6279 0.10668 0.10353 -0.0886 0.0092 1.0000
18.250 1.6104 0.11395 0.11094 -0.0918 0.0092 1.0000
18.500 1.5923 0.12161 0.11873 -0.0955 0.0091 1.0000
18.750 1.5735 0.12961 0.12687 -0.0996 0.0091 1.0000
19.000 1.5544 0.13787 0.13526 -0.1041 0.0091 1.0000
19.250 1.5348 0.14647 0.14400 -0.1091 0.0090 1.0000
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