SARATOV AIRFOIL (saratov-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SARATOV AIRFOIL (saratov-il) Reynolds number: 200,000 Max Cl/Cd: 161.91 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-saratov-il-200000.txt Download as CSV file: xf-saratov-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SARATOV 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.0129 0.09728 0.09271 -0.0987 0.7360 0.0622
-9.250 0.0165 0.09570 0.09088 -0.0993 0.7039 0.0649
-9.000 0.0023 0.09699 0.09210 -0.1023 0.6871 0.0664
-8.750 0.0194 0.09169 0.08666 -0.1017 0.6739 0.0674
-8.500 0.0356 0.08894 0.08376 -0.1009 0.6631 0.0687
-8.250 0.0476 0.08696 0.08173 -0.1009 0.6551 0.0705
-8.000 0.0569 0.08510 0.07978 -0.1013 0.6490 0.0728
-7.750 0.0621 0.08344 0.07810 -0.1026 0.6440 0.0764
-7.500 0.0431 0.08496 0.07969 -0.1063 0.6398 0.0780
-7.250 0.0665 0.07942 0.07406 -0.1044 0.6355 0.0793
-7.000 0.0846 0.07711 0.07164 -0.1039 0.6318 0.0810
-6.750 0.0953 0.07544 0.06996 -0.1038 0.6284 0.0832
-6.500 0.1031 0.07389 0.06841 -0.1046 0.6253 0.0869
-6.250 0.1066 0.07286 0.06740 -0.1141 0.6227 0.0903
-6.000 0.1218 0.06958 0.06407 -0.1107 0.6199 0.0912
-5.750 0.1379 0.06761 0.06204 -0.1098 0.6175 0.0929
-5.500 0.1544 0.06601 0.06037 -0.1106 0.6152 0.0964
-5.250 0.1771 0.06403 0.05836 -0.1225 0.6132 0.1023
-5.000 0.1904 0.06138 0.05572 -0.1199 0.6111 0.1031
-4.750 0.2070 0.05946 0.05379 -0.1192 0.6089 0.1046
-4.500 0.2263 0.05770 0.05201 -0.1203 0.6067 0.1069
-4.000 0.3451 0.02222 0.01491 -0.1778 0.6034 0.0861
-3.750 0.3790 0.01955 0.01169 -0.1813 0.6015 0.0908
-3.500 0.4067 0.01981 0.01200 -0.1809 0.5999 0.0951
-3.250 0.4371 0.01893 0.01088 -0.1821 0.5984 0.1023
-3.000 0.4637 0.01980 0.01200 -0.1811 0.5970 0.1087
-2.750 0.4914 0.02025 0.01253 -0.1807 0.5956 0.1174
-2.500 0.5193 0.02075 0.01306 -0.1804 0.5942 0.1289
-2.250 0.5427 0.02273 0.01528 -0.1780 0.5929 0.1301
-2.000 0.5662 0.02444 0.01712 -0.1760 0.5917 0.1324
-1.750 0.5926 0.02517 0.01787 -0.1754 0.5905 0.1439
-1.500 0.6197 0.02569 0.01836 -0.1751 0.5894 0.1572
-1.250 0.6489 0.02580 0.01835 -0.1756 0.5884 0.1712
-1.000 0.6694 0.02692 0.01962 -0.1735 0.5875 0.1739
-0.750 0.6976 0.02713 0.01976 -0.1738 0.5866 0.1879
-0.500 0.7177 0.02808 0.02084 -0.1718 0.5858 0.1979
-0.250 0.7070 0.01371 0.00709 -0.1593 0.5849 0.2355
0.000 0.7602 0.02905 0.02197 -0.1689 0.5845 0.2413
0.250 0.7559 0.01313 0.00648 -0.1592 0.5831 0.2548
0.500 0.7842 0.01305 0.00635 -0.1601 0.5825 0.2669
0.750 0.8100 0.01294 0.00626 -0.1604 0.5820 0.2746
1.000 0.8409 0.01293 0.00620 -0.1618 0.5815 0.2797
1.250 0.8659 0.01262 0.00594 -0.1622 0.5810 0.2819
1.500 0.8920 0.01258 0.00593 -0.1626 0.5805 0.2868
1.750 0.9229 0.01301 0.00631 -0.1637 0.5800 0.2929
2.000 0.9478 0.01274 0.00610 -0.1641 0.5787 0.2940
2.250 0.9733 0.01263 0.00602 -0.1644 0.5767 0.2955
2.500 0.9999 0.01255 0.00594 -0.1647 0.5744 0.2971
2.750 1.0274 0.01251 0.00590 -0.1652 0.5727 0.2978
3.000 1.0782 0.01055 0.00324 -0.1713 0.5714 0.2348
3.250 1.1041 0.01058 0.00329 -0.1711 0.5696 0.2360
3.500 1.1312 0.01056 0.00325 -0.1711 0.5674 0.2376
3.750 1.1564 0.01072 0.00343 -0.1709 0.5656 0.2396
4.000 1.1797 0.01099 0.00378 -0.1706 0.5642 0.2422
4.250 1.2047 0.01085 0.00361 -0.1708 0.5624 0.2495
4.500 1.2261 0.01142 0.00435 -0.1699 0.5602 0.2513
4.750 1.2491 0.01181 0.00486 -0.1692 0.5577 0.2539
5.000 1.2741 0.01198 0.00509 -0.1689 0.5555 0.2578
5.250 1.3013 0.01185 0.00495 -0.1689 0.5533 0.2650
5.500 1.3299 0.01186 0.00497 -0.1688 0.5504 0.2681
5.750 1.3500 0.01244 0.00571 -0.1677 0.5476 0.2733
6.000 1.3693 0.01296 0.00639 -0.1666 0.5441 0.2800
6.250 1.3920 0.01330 0.00687 -0.1658 0.5408 0.2850
6.500 1.4196 0.01322 0.00684 -0.1656 0.5373 0.2949
6.750 1.4526 0.01276 0.00630 -0.1659 0.5325 0.3072
7.000 1.4699 0.01306 0.00681 -0.1641 0.5246 0.3136
7.250 1.5050 0.01202 0.00565 -0.1644 0.5146 0.3272
7.500 1.5286 0.01153 0.00519 -0.1630 0.5030 0.3403
7.750 1.5486 0.01127 0.00502 -0.1613 0.4917 0.3543
8.000 1.5668 0.01066 0.00444 -0.1590 0.4763 0.3702
8.250 1.5791 0.01016 0.00406 -0.1559 0.4586 0.3844
8.500 1.5867 0.00980 0.00388 -0.1522 0.4325 0.3960
8.750 1.5641 0.00970 0.00329 -0.1433 0.3319 0.3997
9.000 1.5237 0.01166 0.00493 -0.1336 0.2741 0.3992
9.250 1.5679 0.02550 0.01809 -0.1365 0.2361 0.4021
9.500 1.5412 0.02849 0.02094 -0.1303 0.2055 0.4039
9.750 1.5218 0.03154 0.02393 -0.1258 0.1902 0.4071
10.000 1.5069 0.03465 0.02707 -0.1226 0.1800 0.4108
10.250 1.4923 0.03822 0.03068 -0.1201 0.1725 0.4149
10.500 1.4842 0.04149 0.03402 -0.1184 0.1644 0.4201
10.750 1.4739 0.04522 0.03777 -0.1170 0.1574 0.4243
11.000 1.4716 0.04821 0.04084 -0.1159 0.1491 0.4298
11.250 1.4663 0.05162 0.04427 -0.1151 0.1408 0.4345
11.500 1.4679 0.05441 0.04713 -0.1144 0.1272 0.4401
11.750 1.4672 0.05752 0.05021 -0.1139 0.1025 0.4450
12.000 1.4558 0.06182 0.05421 -0.1131 0.0694 0.4478
12.250 1.4483 0.06565 0.05787 -0.1121 0.0544 0.4512
12.500 1.4456 0.06899 0.06115 -0.1113 0.0475 0.4546
12.750 1.4462 0.07195 0.06412 -0.1106 0.0435 0.4590
13.000 1.4459 0.07508 0.06727 -0.1099 0.0408 0.4635
13.250 1.4506 0.07762 0.06989 -0.1092 0.0387 0.4683
13.500 1.4555 0.08012 0.07244 -0.1086 0.0366 0.4725
13.750 1.4594 0.08271 0.07504 -0.1079 0.0349 0.4757
14.000 1.4658 0.08487 0.07719 -0.1069 0.0334 0.4781
14.250 1.4754 0.08676 0.07918 -0.1062 0.0320 0.4803
14.500 1.4858 0.08848 0.08095 -0.1053 0.0309 0.4817
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