Eiffel 385 (S.T. Ae) (eiffel385-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 385 (S.T. Ae) (eiffel385-il) Reynolds number: 500,000 Max Cl/Cd: 106.4 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel385-il-500000.txt Download as CSV file: xf-eiffel385-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 385 (S.T. Ae)
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
------ -------- --------- --------- -------- -------- --------
-18.750 -0.7168 0.09369 0.09052 -0.0686 1.0000 0.0349
-18.500 -0.7632 0.08229 0.07893 -0.0769 1.0000 0.0349
-18.250 -0.7924 0.07449 0.07099 -0.0826 1.0000 0.0349
-18.000 -0.8159 0.06818 0.06457 -0.0869 1.0000 0.0350
-17.750 -0.8382 0.06240 0.05868 -0.0906 1.0000 0.0351
-17.500 -0.8563 0.05756 0.05376 -0.0933 1.0000 0.0352
-17.250 -0.8717 0.05335 0.04949 -0.0952 1.0000 0.0355
-17.000 -0.8870 0.04933 0.04543 -0.0968 1.0000 0.0356
-16.750 -0.9056 0.04523 0.04127 -0.0984 1.0000 0.0357
-16.500 -0.9317 0.04094 0.03693 -0.0997 1.0000 0.0358
-16.250 -0.9676 0.03545 0.03128 -0.1027 1.0000 0.0357
-16.000 -0.9797 0.03322 0.02896 -0.1009 1.0000 0.0359
-15.750 -0.9848 0.03153 0.02721 -0.0986 1.0000 0.0362
-15.500 -0.9681 0.02987 0.02548 -0.0994 0.9985 0.0367
-15.250 -0.9384 0.02828 0.02380 -0.1020 0.9956 0.0375
-15.000 -0.9067 0.02676 0.02214 -0.1047 0.9932 0.0382
-14.750 -0.8794 0.02539 0.02065 -0.1061 0.9894 0.0389
-14.500 -0.8493 0.02419 0.01930 -0.1076 0.9863 0.0395
-14.250 -0.8173 0.02316 0.01813 -0.1093 0.9839 0.0400
-14.000 -0.7873 0.02159 0.01651 -0.1111 0.9819 0.0411
-13.750 -0.7632 0.02062 0.01550 -0.1110 0.9772 0.0420
-13.500 -0.7335 0.01975 0.01457 -0.1119 0.9739 0.0429
-13.250 -0.7008 0.01893 0.01366 -0.1131 0.9716 0.0439
-13.000 -0.6662 0.01814 0.01278 -0.1146 0.9698 0.0449
-12.750 -0.6367 0.01749 0.01202 -0.1149 0.9662 0.0458
-12.500 -0.6102 0.01652 0.01103 -0.1150 0.9613 0.0473
-12.250 -0.5773 0.01580 0.01027 -0.1161 0.9588 0.0491
-12.000 -0.5422 0.01517 0.00957 -0.1174 0.9569 0.0510
-11.750 -0.5062 0.01444 0.00878 -0.1190 0.9554 0.0532
-11.500 -0.4786 0.01382 0.00815 -0.1188 0.9502 0.0563
-11.250 -0.4468 0.01321 0.00751 -0.1194 0.9459 0.0609
-11.000 -0.4125 0.01260 0.00694 -0.1205 0.9428 0.0699
-10.750 -0.3759 0.01223 0.00661 -0.1219 0.9401 0.0838
-10.500 -0.3474 0.01204 0.00642 -0.1216 0.9332 0.0928
-10.000 -0.2782 0.01158 0.00586 -0.1234 0.9227 0.1047
-9.750 -0.2519 0.01137 0.00559 -0.1226 0.9132 0.1085
-9.500 -0.2184 0.01104 0.00524 -0.1234 0.9065 0.1133
-9.250 -0.1922 0.01088 0.00502 -0.1226 0.8955 0.1170
-9.000 -0.1623 0.01070 0.00475 -0.1226 0.8858 0.1202
-8.750 -0.1352 0.01040 0.00444 -0.1221 0.8741 0.1244
-8.500 -0.1085 0.01022 0.00421 -0.1214 0.8613 0.1279
-8.250 -0.0812 0.01007 0.00398 -0.1208 0.8475 0.1310
-8.000 -0.0545 0.00990 0.00374 -0.1202 0.8323 0.1351
-7.750 -0.0283 0.00977 0.00358 -0.1194 0.8153 0.1406
-7.500 -0.0021 0.00970 0.00342 -0.1186 0.7964 0.1455
-7.250 0.0235 0.00961 0.00329 -0.1178 0.7766 0.1514
-7.000 0.0495 0.00961 0.00320 -0.1170 0.7574 0.1580
-6.750 0.0754 0.00961 0.00314 -0.1162 0.7398 0.1650
-6.500 0.1018 0.00967 0.00311 -0.1155 0.7243 0.1730
-6.250 0.1280 0.00969 0.00308 -0.1148 0.7112 0.1807
-6.000 0.1549 0.00980 0.00310 -0.1142 0.6991 0.1887
-5.750 0.1814 0.00980 0.00306 -0.1136 0.6886 0.1955
-5.250 0.2352 0.01000 0.00309 -0.1125 0.6684 0.2066
-5.000 0.2612 0.00994 0.00300 -0.1119 0.6600 0.2124
-4.750 0.2884 0.00994 0.00300 -0.1115 0.6528 0.2170
-4.500 0.3154 0.00999 0.00299 -0.1111 0.6460 0.2210
-4.250 0.3429 0.01007 0.00299 -0.1107 0.6398 0.2238
-4.000 0.3693 0.00993 0.00289 -0.1102 0.6335 0.2282
-3.750 0.3962 0.00993 0.00286 -0.1098 0.6274 0.2318
-3.500 0.4233 0.00995 0.00286 -0.1095 0.6217 0.2351
-3.250 0.4504 0.00994 0.00285 -0.1091 0.6160 0.2381
-3.000 0.4774 0.00998 0.00285 -0.1087 0.6101 0.2407
-2.750 0.5042 0.00997 0.00283 -0.1083 0.6045 0.2445
-2.500 0.5307 0.00991 0.00282 -0.1079 0.5987 0.2484
-2.250 0.5574 0.00992 0.00283 -0.1075 0.5929 0.2523
-2.000 0.5843 0.00998 0.00285 -0.1072 0.5873 0.2559
-1.750 0.6109 0.00996 0.00286 -0.1067 0.5812 0.2590
-1.500 0.6372 0.00993 0.00286 -0.1063 0.5752 0.2632
-1.250 0.6636 0.00997 0.00290 -0.1059 0.5693 0.2677
-1.000 0.6897 0.00994 0.00293 -0.1054 0.5627 0.2729
-0.750 0.7157 0.00995 0.00296 -0.1049 0.5559 0.2799
-0.500 0.7416 0.00996 0.00303 -0.1045 0.5495 0.2913
-0.250 0.7673 0.00993 0.00310 -0.1040 0.5422 0.3089
0.000 0.7925 0.00997 0.00319 -0.1034 0.5349 0.3370
0.250 0.8180 0.00994 0.00329 -0.1029 0.5265 0.3702
0.500 0.8423 0.01000 0.00335 -0.1021 0.5172 0.3970
0.750 0.8672 0.00998 0.00342 -0.1015 0.5067 0.4200
1.000 0.8909 0.00999 0.00350 -0.1007 0.4960 0.4445
1.250 0.9135 0.00997 0.00359 -0.0997 0.4840 0.4877
1.500 0.9737 0.00923 0.00391 -0.1071 0.4667 1.0000
1.750 0.9972 0.00940 0.00403 -0.1062 0.4533 1.0000
2.000 1.0204 0.00959 0.00417 -0.1053 0.4403 1.0000
2.250 1.0428 0.00981 0.00433 -0.1043 0.4270 1.0000
2.500 1.0644 0.01007 0.00450 -0.1032 0.4110 1.0000
2.750 1.0856 0.01034 0.00470 -0.1020 0.3950 1.0000
3.000 1.1066 0.01063 0.00491 -0.1008 0.3804 1.0000
3.250 1.1281 0.01091 0.00513 -0.0997 0.3677 1.0000
3.500 1.1499 0.01117 0.00536 -0.0987 0.3562 1.0000
3.750 1.1706 0.01147 0.00561 -0.0975 0.3450 1.0000
4.000 1.1908 0.01178 0.00587 -0.0963 0.3334 1.0000
4.250 1.2114 0.01207 0.00613 -0.0951 0.3212 1.0000
4.500 1.2312 0.01238 0.00641 -0.0938 0.3108 1.0000
4.750 1.2500 0.01271 0.00670 -0.0923 0.3007 1.0000
5.000 1.2690 0.01299 0.00698 -0.0909 0.2912 1.0000
5.250 1.2854 0.01335 0.00730 -0.0890 0.2807 1.0000
5.500 1.3027 0.01368 0.00762 -0.0873 0.2689 1.0000
5.750 1.3194 0.01406 0.00797 -0.0856 0.2560 1.0000
6.000 1.3343 0.01452 0.00837 -0.0836 0.2397 1.0000
6.250 1.3463 0.01512 0.00887 -0.0812 0.2190 1.0000
6.500 1.3550 0.01591 0.00950 -0.0784 0.1892 1.0000
6.750 1.3532 0.01727 0.01055 -0.0743 0.1405 1.0000
7.000 1.3502 0.01879 0.01182 -0.0703 0.1054 1.0000
7.250 1.3539 0.02003 0.01295 -0.0674 0.0862 1.0000
7.500 1.3616 0.02109 0.01396 -0.0651 0.0772 1.0000
7.750 1.3698 0.02217 0.01503 -0.0631 0.0720 1.0000
8.000 1.3797 0.02319 0.01608 -0.0614 0.0689 1.0000
8.250 1.3873 0.02440 0.01730 -0.0597 0.0663 1.0000
8.500 1.3930 0.02580 0.01873 -0.0579 0.0637 1.0000
8.750 1.4029 0.02697 0.01997 -0.0566 0.0621 1.0000
9.000 1.4110 0.02831 0.02137 -0.0554 0.0604 1.0000
9.250 1.4168 0.02991 0.02301 -0.0541 0.0589 1.0000
9.500 1.4194 0.03183 0.02499 -0.0528 0.0573 1.0000
9.750 1.4182 0.03419 0.02741 -0.0515 0.0559 1.0000
10.000 1.4244 0.03598 0.02928 -0.0508 0.0550 1.0000
10.250 1.4315 0.03775 0.03113 -0.0502 0.0539 1.0000
10.500 1.4359 0.03981 0.03326 -0.0496 0.0529 1.0000
10.750 1.4396 0.04202 0.03554 -0.0492 0.0518 1.0000
11.000 1.4414 0.04445 0.03805 -0.0488 0.0509 1.0000
11.250 1.4402 0.04725 0.04089 -0.0484 0.0498 1.0000
11.500 1.4354 0.05045 0.04415 -0.0480 0.0489 1.0000
11.750 1.4353 0.05320 0.04697 -0.0477 0.0479 1.0000
12.000 1.4397 0.05554 0.04941 -0.0477 0.0472 1.0000
12.250 1.4431 0.05803 0.05198 -0.0477 0.0462 1.0000
12.500 1.4450 0.06072 0.05474 -0.0478 0.0452 1.0000
12.750 1.4461 0.06352 0.05761 -0.0479 0.0444 1.0000
13.000 1.4459 0.06651 0.06064 -0.0482 0.0434 1.0000
13.250 1.4426 0.06983 0.06400 -0.0483 0.0426 1.0000
13.500 1.4390 0.07314 0.06736 -0.0483 0.0416 1.0000
13.750 1.4421 0.07600 0.07034 -0.0489 0.0407 1.0000
14.000 1.4430 0.07904 0.07347 -0.0494 0.0399 1.0000
14.250 1.4439 0.08215 0.07666 -0.0501 0.0389 1.0000
14.500 1.4436 0.08542 0.07999 -0.0507 0.0380 1.0000
14.750 1.4423 0.08886 0.08348 -0.0515 0.0372 1.0000
15.000 1.4391 0.09235 0.08697 -0.0520 0.0363 1.0000
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Polar data table (+)
Polar graphs
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