Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Supermarine 371-I (root) (supermarine371i-il) Reynolds number: 50,000 Max Cl/Cd: 28.6 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-supermarine371i-il-50000.txt Download as CSV file: xf-supermarine371i-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-I (root)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4278 0.10429 0.09715 -0.0165 1.0000 0.3634
-9.500 -0.6172 0.07753 0.07084 -0.0484 1.0000 0.1576
-9.250 -0.6238 0.07310 0.06645 -0.0476 1.0000 0.1528
-9.000 -0.6814 0.06930 0.06252 -0.0436 1.0000 0.1426
-8.750 -0.6951 0.06647 0.05967 -0.0401 1.0000 0.1405
-8.500 -0.7159 0.06402 0.05714 -0.0355 1.0000 0.1382
-8.250 -0.7688 0.06190 0.05435 -0.0275 1.0000 0.1298
-8.000 -0.7743 0.05897 0.05124 -0.0241 1.0000 0.1293
-7.750 -0.7779 0.05602 0.04808 -0.0207 1.0000 0.1288
-7.500 -0.7798 0.05310 0.04488 -0.0174 1.0000 0.1284
-7.250 -0.7787 0.05015 0.04159 -0.0143 1.0000 0.1278
-7.000 -0.7744 0.04728 0.03835 -0.0115 1.0000 0.1273
-6.750 -0.7667 0.04457 0.03523 -0.0089 1.0000 0.1274
-6.500 -0.7577 0.04219 0.03227 -0.0061 1.0000 0.1292
-6.250 -0.7428 0.03964 0.02964 -0.0046 1.0000 0.1338
-6.000 -0.7265 0.03763 0.02739 -0.0028 1.0000 0.1394
-5.750 -0.7086 0.03569 0.02491 -0.0009 1.0000 0.1441
-5.500 -0.6877 0.03380 0.02309 0.0001 1.0000 0.1543
-5.250 -0.6656 0.03212 0.02131 0.0012 1.0000 0.1667
-5.000 -0.6427 0.03063 0.01979 0.0024 1.0000 0.1859
-4.750 -0.6191 0.02903 0.01841 0.0037 1.0000 0.2165
-4.500 -0.6022 0.02715 0.01706 0.0058 1.0000 0.2735
-4.250 -0.5942 0.02498 0.01582 0.0090 1.0000 0.3681
-4.000 -0.5967 0.02410 0.01708 0.0182 1.0000 0.6413
-3.750 -0.5962 0.02583 0.01877 0.0281 1.0000 0.7682
-3.500 -0.5590 0.02891 0.02153 0.0342 1.0000 0.8494
-3.250 -0.3523 0.03322 0.02459 0.0095 1.0000 0.9224
-3.000 -0.1793 0.03329 0.02384 -0.0165 1.0000 0.9791
-2.750 -0.1065 0.03249 0.02271 -0.0273 1.0000 1.0000
-2.500 -0.1048 0.03225 0.02238 -0.0249 1.0000 1.0000
-2.250 -0.1025 0.03204 0.02207 -0.0225 1.0000 1.0000
-2.000 -0.0996 0.03185 0.02178 -0.0200 1.0000 1.0000
-1.750 -0.0962 0.03168 0.02153 -0.0176 1.0000 1.0000
-1.500 -0.0924 0.03152 0.02129 -0.0152 1.0000 1.0000
-1.250 -0.0884 0.03138 0.02108 -0.0128 1.0000 1.0000
-1.000 -0.0842 0.03125 0.02089 -0.0104 1.0000 1.0000
-0.750 -0.0800 0.03113 0.02070 -0.0079 1.0000 1.0000
-0.500 -0.0758 0.03102 0.02052 -0.0054 1.0000 1.0000
-0.250 -0.0717 0.03091 0.02036 -0.0029 1.0000 1.0000
0.000 -0.0679 0.03080 0.02021 -0.0003 1.0000 1.0000
0.250 -0.0644 0.03068 0.02006 0.0023 1.0000 1.0000
0.500 -0.0613 0.03056 0.01990 0.0050 1.0000 1.0000
0.750 -0.0586 0.03042 0.01973 0.0077 1.0000 1.0000
1.000 -0.0565 0.03028 0.01957 0.0106 1.0000 1.0000
1.250 -0.0549 0.03012 0.01939 0.0135 1.0000 1.0000
1.500 -0.0535 0.02996 0.01921 0.0164 1.0000 1.0000
1.750 -0.0513 0.02983 0.01906 0.0192 1.0000 1.0000
2.000 -0.0473 0.02979 0.01898 0.0216 1.0000 1.0000
2.250 -0.0410 0.02986 0.01903 0.0237 1.0000 1.0000
2.500 -0.0321 0.03009 0.01922 0.0252 1.0000 1.0000
2.750 -0.0209 0.03045 0.01955 0.0263 1.0000 1.0000
3.000 -0.0083 0.03093 0.02002 0.0271 1.0000 1.0000
3.250 0.0052 0.03151 0.02060 0.0277 1.0000 1.0000
3.500 0.0192 0.03218 0.02127 0.0281 1.0000 1.0000
3.750 0.0566 0.03386 0.02302 0.0238 0.9893 1.0000
4.000 0.1288 0.03679 0.02611 0.0134 0.9573 1.0000
4.250 0.1749 0.03847 0.02792 0.0083 0.9307 1.0000
4.500 0.2198 0.04004 0.02965 0.0040 0.9031 1.0000
4.750 0.2649 0.04146 0.03124 0.0001 0.8741 1.0000
5.000 0.3098 0.04265 0.03262 -0.0033 0.8449 1.0000
5.250 0.3553 0.04360 0.03379 -0.0062 0.8155 1.0000
5.500 0.4024 0.04418 0.03463 -0.0088 0.7858 1.0000
5.750 0.4485 0.04420 0.03494 -0.0104 0.7535 1.0000
6.000 0.5024 0.04322 0.03430 -0.0116 0.7180 1.0000
6.250 0.6004 0.03927 0.03102 -0.0151 0.6810 1.0000
6.500 0.6622 0.03471 0.02700 -0.0131 0.6385 1.0000
6.750 0.7129 0.02913 0.02188 -0.0080 0.5747 1.0000
7.000 0.7561 0.02644 0.01758 -0.0016 0.3699 1.0000
7.250 0.7613 0.02853 0.01881 0.0024 0.2931 1.0000
7.500 0.7832 0.03062 0.02041 0.0036 0.2372 1.0000
7.750 0.8192 0.03294 0.02233 0.0029 0.1966 1.0000
8.000 0.8497 0.03517 0.02451 0.0028 0.1718 1.0000
8.250 0.8817 0.03782 0.02705 0.0023 0.1546 1.0000
8.500 0.9001 0.04007 0.02966 0.0039 0.1439 1.0000
8.750 0.9196 0.04292 0.03275 0.0050 0.1362 1.0000
9.000 0.9340 0.04575 0.03595 0.0068 0.1310 1.0000
9.250 0.9545 0.04906 0.03923 0.0073 0.1250 1.0000
9.500 0.9543 0.05197 0.04271 0.0106 0.1227 1.0000
9.750 0.9545 0.05540 0.04658 0.0134 0.1217 1.0000
10.000 0.9513 0.05907 0.05063 0.0162 0.1217 1.0000
10.250 0.9426 0.06281 0.05470 0.0191 0.1220 1.0000
10.500 0.9295 0.06663 0.05879 0.0219 0.1225 1.0000
10.750 0.9143 0.07046 0.06283 0.0245 0.1233 1.0000
11.000 0.8967 0.07435 0.06685 0.0269 0.1240 1.0000
11.250 0.8834 0.07876 0.07136 0.0281 0.1249 1.0000
11.500 0.8730 0.08364 0.07632 0.0287 0.1255 1.0000
11.750 0.7581 0.09437 0.08725 0.0232 0.1373 1.0000
12.000 0.7687 0.09962 0.09252 0.0230 0.1397 1.0000
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Polar data table (+)
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