I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 960 (isa960-il) Reynolds number: 500,000 Max Cl/Cd: 68.19 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa960-il-500000.txt Download as CSV file: xf-isa960-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 960
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3419 0.08933 0.08725 -0.0349 0.9982 0.0254
-9.250 -0.3346 0.08306 0.08101 -0.0434 0.9815 0.0266
-8.750 -0.3839 0.02768 0.02438 -0.0931 0.9560 0.0176
-8.500 -0.3568 0.02425 0.02051 -0.0953 0.9424 0.0181
-8.250 -0.3307 0.02180 0.01766 -0.0962 0.9283 0.0188
-7.750 -0.2814 0.01889 0.01400 -0.0956 0.8981 0.0204
-7.500 -0.2583 0.01720 0.01191 -0.0950 0.8809 0.0214
-7.250 -0.2346 0.01590 0.01044 -0.0944 0.8609 0.0225
-7.000 -0.2097 0.01514 0.00950 -0.0937 0.8354 0.0235
-6.750 -0.1850 0.01449 0.00857 -0.0929 0.7950 0.0247
-6.500 -0.1604 0.01403 0.00776 -0.0920 0.7501 0.0259
-6.250 -0.1351 0.01338 0.00680 -0.0913 0.7198 0.0274
-6.000 -0.1100 0.01262 0.00583 -0.0908 0.6889 0.0297
-5.750 -0.0840 0.01226 0.00525 -0.0904 0.6496 0.0316
-5.500 -0.0597 0.01221 0.00474 -0.0896 0.5551 0.0334
-5.250 -0.0363 0.01222 0.00421 -0.0888 0.4445 0.0360
-5.000 -0.0149 0.01285 0.00403 -0.0880 0.2243 0.0392
-4.750 0.0125 0.01266 0.00369 -0.0878 0.2075 0.0423
-4.500 0.0401 0.01243 0.00344 -0.0876 0.1968 0.0497
-4.250 0.0679 0.01234 0.00337 -0.0875 0.1873 0.0660
-4.000 0.0958 0.01234 0.00329 -0.0874 0.1743 0.0801
-3.750 0.1228 0.01249 0.00326 -0.0872 0.1278 0.0886
-3.500 0.1504 0.01243 0.00317 -0.0871 0.1254 0.0956
-3.250 0.1783 0.01243 0.00313 -0.0870 0.1235 0.1005
-3.000 0.2061 0.01240 0.00306 -0.0869 0.1225 0.1055
-2.750 0.2339 0.01238 0.00304 -0.0869 0.1217 0.1111
-2.500 0.2617 0.01240 0.00302 -0.0868 0.1211 0.1159
-2.250 0.2895 0.01235 0.00298 -0.0867 0.1207 0.1214
-2.000 0.3173 0.01237 0.00299 -0.0866 0.1203 0.1289
-1.750 0.3450 0.01236 0.00300 -0.0865 0.1198 0.1390
-1.500 0.3726 0.01235 0.00301 -0.0865 0.1192 0.1529
-1.250 0.4001 0.01235 0.00303 -0.0864 0.1188 0.1676
-1.000 0.4277 0.01236 0.00305 -0.0863 0.1185 0.1806
-0.750 0.4552 0.01237 0.00309 -0.0863 0.1184 0.1946
-0.500 0.4825 0.01237 0.00315 -0.0862 0.1184 0.2151
-0.250 0.5098 0.01233 0.00325 -0.0862 0.1183 0.2605
0.000 0.5365 0.01206 0.00337 -0.0862 0.1183 0.4014
0.250 0.5627 0.01075 0.00354 -0.0858 0.1183 1.0000
0.500 0.5896 0.01092 0.00364 -0.0856 0.1183 1.0000
0.750 0.6164 0.01109 0.00376 -0.0855 0.1184 1.0000
1.000 0.6431 0.01127 0.00389 -0.0853 0.1184 1.0000
1.250 0.6698 0.01146 0.00403 -0.0851 0.1185 1.0000
1.500 0.6963 0.01166 0.00419 -0.0849 0.1186 1.0000
1.750 0.7227 0.01186 0.00436 -0.0846 0.1187 1.0000
2.000 0.7491 0.01207 0.00454 -0.0844 0.1188 1.0000
2.250 0.7753 0.01229 0.00474 -0.0842 0.1190 1.0000
2.500 0.8014 0.01252 0.00495 -0.0840 0.1191 1.0000
2.750 0.8274 0.01275 0.00516 -0.0837 0.1193 1.0000
3.000 0.8533 0.01298 0.00539 -0.0835 0.1194 1.0000
3.250 0.8790 0.01323 0.00562 -0.0832 0.1196 1.0000
3.500 0.9047 0.01348 0.00588 -0.0829 0.1198 1.0000
3.750 0.9301 0.01373 0.00613 -0.0826 0.1200 1.0000
4.000 0.9553 0.01401 0.00641 -0.0823 0.1201 1.0000
4.250 0.9796 0.01437 0.00678 -0.0818 0.1196 1.0000
4.500 1.0034 0.01477 0.00719 -0.0813 0.1190 1.0000
4.750 1.0271 0.01518 0.00760 -0.0807 0.1186 1.0000
5.000 1.0513 0.01552 0.00796 -0.0803 0.1186 1.0000
5.250 1.0744 0.01597 0.00844 -0.0797 0.1181 1.0000
5.500 1.0971 0.01646 0.00896 -0.0790 0.1166 1.0000
5.750 1.1210 0.01678 0.00932 -0.0786 0.1149 1.0000
6.000 1.1440 0.01721 0.00977 -0.0780 0.1137 1.0000
6.250 1.1662 0.01770 0.01030 -0.0773 0.1120 1.0000
6.500 1.1867 0.01841 0.01099 -0.0764 0.1094 1.0000
6.750 1.2067 0.01937 0.01191 -0.0756 0.1075 1.0000
7.000 1.2283 0.02017 0.01274 -0.0749 0.1056 1.0000
7.250 1.2508 0.02019 0.01288 -0.0742 0.1033 1.0000
7.500 1.2722 0.02051 0.01326 -0.0735 0.1003 1.0000
7.750 1.2917 0.02117 0.01391 -0.0726 0.0970 1.0000
8.000 1.3124 0.02126 0.01413 -0.0717 0.0930 1.0000
8.250 1.3475 0.02002 0.01300 -0.0729 0.0836 1.0000
8.750 1.3876 0.02094 0.01346 -0.0710 0.0198 1.0000
9.000 1.4011 0.02168 0.01428 -0.0689 0.0179 1.0000
9.250 1.4138 0.02248 0.01517 -0.0668 0.0169 1.0000
9.500 1.4245 0.02345 0.01623 -0.0646 0.0159 1.0000
9.750 1.4323 0.02464 0.01751 -0.0621 0.0150 1.0000
10.000 1.4355 0.02621 0.01921 -0.0593 0.0141 1.0000
10.250 1.4422 0.02757 0.02068 -0.0572 0.0137 1.0000
10.500 1.4493 0.02897 0.02218 -0.0553 0.0134 1.0000
10.750 1.4546 0.03056 0.02388 -0.0534 0.0130 1.0000
11.000 1.4583 0.03235 0.02579 -0.0516 0.0127 1.0000
11.250 1.4606 0.03436 0.02790 -0.0500 0.0124 1.0000
11.500 1.4615 0.03658 0.03025 -0.0485 0.0121 1.0000
11.750 1.4612 0.03905 0.03283 -0.0473 0.0118 1.0000
12.000 1.4594 0.04178 0.03567 -0.0463 0.0116 1.0000
12.250 1.4561 0.04481 0.03881 -0.0456 0.0114 1.0000
12.500 1.4507 0.04816 0.04226 -0.0450 0.0112 1.0000
12.750 1.4430 0.05188 0.04609 -0.0446 0.0110 1.0000
13.000 1.4334 0.05592 0.05023 -0.0443 0.0108 1.0000
13.250 1.4212 0.06034 0.05476 -0.0441 0.0106 1.0000
13.500 1.4107 0.06466 0.05919 -0.0439 0.0105 1.0000
13.750 1.4104 0.06809 0.06276 -0.0446 0.0103 1.0000
14.000 1.4080 0.07182 0.06661 -0.0453 0.0102 1.0000
14.250 1.4043 0.07580 0.07070 -0.0461 0.0100 1.0000
14.500 1.3996 0.07995 0.07498 -0.0469 0.0099 1.0000
14.750 1.3947 0.08419 0.07933 -0.0478 0.0098 1.0000
15.000 1.3894 0.08853 0.08380 -0.0489 0.0097 1.0000
15.250 1.3840 0.09298 0.08837 -0.0501 0.0096 1.0000
15.500 1.3784 0.09752 0.09303 -0.0513 0.0095 1.0000
15.750 1.3725 0.10215 0.09777 -0.0527 0.0094 1.0000
16.000 1.3664 0.10689 0.10263 -0.0543 0.0093 1.0000
16.250 1.3601 0.11175 0.10760 -0.0560 0.0092 1.0000
16.500 1.3536 0.11674 0.11272 -0.0579 0.0092 1.0000
16.750 1.3469 0.12188 0.11798 -0.0601 0.0091 1.0000
17.000 1.3399 0.12716 0.12338 -0.0624 0.0090 1.0000
17.250 1.3323 0.13265 0.12901 -0.0650 0.0090 1.0000
17.500 1.3245 0.13838 0.13486 -0.0679 0.0090 1.0000
17.750 1.3160 0.14441 0.14103 -0.0712 0.0089 1.0000
18.000 1.3071 0.15071 0.14746 -0.0748 0.0089 1.0000
18.250 1.2970 0.15748 0.15438 -0.0788 0.0089 1.0000
18.500 1.2857 0.16474 0.16179 -0.0832 0.0090 1.0000
18.750 1.2730 0.17258 0.16978 -0.0881 0.0090 1.0000
19.000 1.2595 0.18103 0.17838 -0.0936 0.0091 1.0000
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Polar data table (+)
Polar graphs
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