FX S 03-182 AIRFOIL (fxs03182-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 03-182 AIRFOIL (fxs03182-il) Reynolds number: 500,000 Max Cl/Cd: 89.48 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs03182-il-500000-n5.txt Download as CSV file: xf-fxs03182-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX S 03-182 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.4842 0.10495 0.10246 -0.0706 0.9815 0.0030
-15.000 -0.5284 0.08780 0.08507 -0.0804 0.9713 0.0029
-14.750 -0.5465 0.07620 0.07323 -0.0903 0.9582 0.0029
-14.500 -0.5506 0.06705 0.06382 -0.1003 0.9466 0.0028
-14.250 -0.5480 0.05887 0.05533 -0.1107 0.9356 0.0028
-14.000 -0.5395 0.05195 0.04807 -0.1205 0.9210 0.0028
-13.750 -0.5297 0.04665 0.04240 -0.1278 0.9006 0.0028
-13.500 -0.5246 0.04337 0.03882 -0.1306 0.8767 0.0028
-13.250 -0.5242 0.04086 0.03606 -0.1311 0.8563 0.0028
-13.000 -0.5235 0.03876 0.03373 -0.1309 0.8402 0.0028
-12.750 -0.5234 0.03668 0.03143 -0.1302 0.8266 0.0028
-12.500 -0.5207 0.03490 0.02946 -0.1295 0.8144 0.0028
-12.250 -0.5183 0.03306 0.02741 -0.1284 0.8039 0.0029
-12.000 -0.5100 0.03186 0.02608 -0.1277 0.7941 0.0028
-11.750 -0.5031 0.03047 0.02454 -0.1267 0.7852 0.0028
-11.500 -0.4946 0.02922 0.02315 -0.1257 0.7776 0.0028
-11.250 -0.4865 0.02794 0.02172 -0.1246 0.7702 0.0029
-11.000 -0.4751 0.02696 0.02064 -0.1237 0.7637 0.0029
-10.750 -0.4647 0.02589 0.01945 -0.1226 0.7571 0.0029
-10.500 -0.4540 0.02488 0.01832 -0.1214 0.7512 0.0030
-10.250 -0.4418 0.02398 0.01734 -0.1204 0.7453 0.0030
-10.000 -0.4300 0.02308 0.01634 -0.1191 0.7399 0.0031
-9.750 -0.4171 0.02227 0.01544 -0.1180 0.7348 0.0031
-9.500 -0.4039 0.02150 0.01459 -0.1169 0.7295 0.0031
-9.250 -0.3917 0.02071 0.01370 -0.1155 0.7246 0.0032
-9.000 -0.3775 0.02004 0.01297 -0.1144 0.7201 0.0033
-8.750 -0.3641 0.01934 0.01220 -0.1131 0.7154 0.0033
-8.500 -0.3503 0.01871 0.01149 -0.1118 0.7112 0.0033
-8.250 -0.3366 0.01808 0.01079 -0.1104 0.7075 0.0034
-8.000 -0.3221 0.01752 0.01018 -0.1091 0.7038 0.0035
-7.750 -0.3106 0.01687 0.00946 -0.1073 0.7000 0.0037
-7.500 -0.3044 0.01621 0.00870 -0.1046 0.6965 0.0039
-7.250 -0.2917 0.01575 0.00818 -0.1029 0.6935 0.0040
-7.000 -0.2750 0.01529 0.00766 -0.1018 0.6904 0.0041
-6.750 -0.2576 0.01483 0.00712 -0.1007 0.6873 0.0046
-6.500 -0.2373 0.01449 0.00673 -0.1000 0.6845 0.0047
-6.250 -0.2165 0.01416 0.00631 -0.0994 0.6818 0.0051
-6.000 -0.1941 0.01387 0.00595 -0.0989 0.6793 0.0054
-5.750 -0.1726 0.01345 0.00554 -0.0985 0.6766 0.0075
-5.500 -0.1488 0.01318 0.00527 -0.0983 0.6739 0.0143
-5.250 -0.1238 0.01298 0.00504 -0.0982 0.6715 0.0162
-5.000 -0.0988 0.01277 0.00481 -0.0982 0.6693 0.0187
-4.750 -0.0730 0.01261 0.00459 -0.0982 0.6673 0.0205
-4.500 -0.0474 0.01239 0.00438 -0.0983 0.6655 0.0255
-4.250 -0.0215 0.01214 0.00418 -0.0985 0.6635 0.0363
-4.000 0.0054 0.01200 0.00402 -0.0988 0.6615 0.0411
-3.750 0.0313 0.01168 0.00379 -0.0990 0.6596 0.0677
-3.500 0.0567 0.01119 0.00352 -0.0994 0.6577 0.1272
-3.250 0.0821 0.01049 0.00317 -0.1001 0.6559 0.2282
-3.000 0.1084 0.00901 0.00253 -0.1020 0.6542 0.4561
-2.750 0.1377 0.00883 0.00260 -0.1028 0.6525 0.5435
-2.500 0.1673 0.00888 0.00265 -0.1034 0.6508 0.5667
-2.250 0.1967 0.00892 0.00268 -0.1039 0.6491 0.5773
-2.000 0.2260 0.00896 0.00270 -0.1044 0.6474 0.5843
-1.750 0.2555 0.00901 0.00273 -0.1049 0.6458 0.5918
-1.500 0.2847 0.00908 0.00281 -0.1054 0.6442 0.6000
-1.250 0.3143 0.00917 0.00285 -0.1060 0.6427 0.6084
-1.000 0.3432 0.00923 0.00292 -0.1064 0.6413 0.6132
-0.750 0.3724 0.00928 0.00296 -0.1069 0.6399 0.6166
-0.500 0.4018 0.00934 0.00298 -0.1074 0.6386 0.6199
0.000 0.4604 0.00942 0.00303 -0.1085 0.6357 0.6249
0.250 0.4893 0.00944 0.00307 -0.1090 0.6342 0.6260
0.500 0.5184 0.00947 0.00311 -0.1095 0.6328 0.6271
0.750 0.5474 0.00950 0.00316 -0.1101 0.6314 0.6282
1.000 0.5761 0.00952 0.00319 -0.1105 0.6292 0.6294
1.250 0.6044 0.00954 0.00319 -0.1108 0.6255 0.6306
1.500 0.6326 0.00957 0.00321 -0.1111 0.6215 0.6320
1.750 0.6606 0.00958 0.00326 -0.1114 0.6180 0.6335
2.000 0.6887 0.00961 0.00329 -0.1118 0.6143 0.6350
2.250 0.7166 0.00964 0.00330 -0.1120 0.6098 0.6364
2.500 0.7429 0.00964 0.00331 -0.1119 0.6011 0.6377
2.750 0.7685 0.00966 0.00331 -0.1117 0.5910 0.6389
3.000 0.7951 0.00968 0.00337 -0.1117 0.5835 0.6401
3.250 0.8215 0.00972 0.00344 -0.1116 0.5757 0.6413
3.500 0.8469 0.00978 0.00349 -0.1114 0.5653 0.6426
3.750 0.8716 0.00985 0.00356 -0.1110 0.5507 0.6441
4.000 0.8939 0.00999 0.00366 -0.1102 0.5253 0.6457
4.250 0.9049 0.01049 0.00389 -0.1073 0.4679 0.6475
4.500 0.9008 0.01161 0.00458 -0.1018 0.3868 0.6493
4.750 0.8899 0.01276 0.00534 -0.0950 0.3108 0.6511
5.000 0.8866 0.01381 0.00612 -0.0900 0.2536 0.6527
5.250 0.8797 0.01507 0.00709 -0.0847 0.1917 0.6542
5.750 0.8720 0.01773 0.00929 -0.0762 0.0897 0.6575
6.000 0.8804 0.01867 0.01015 -0.0740 0.0651 0.6593
6.250 0.8887 0.01967 0.01108 -0.0719 0.0458 0.6612
6.500 0.9018 0.02047 0.01186 -0.0705 0.0344 0.6632
6.750 0.9151 0.02129 0.01266 -0.0692 0.0294 0.6653
7.000 0.9305 0.02202 0.01341 -0.0681 0.0244 0.6675
7.500 0.9546 0.02393 0.01535 -0.0655 0.0120 0.6717
7.750 0.9682 0.02483 0.01629 -0.0644 0.0102 0.6739
8.000 0.9832 0.02566 0.01715 -0.0635 0.0093 0.6763
8.250 0.9988 0.02648 0.01800 -0.0627 0.0090 0.6787
8.500 1.0143 0.02732 0.01888 -0.0620 0.0081 0.6812
8.750 1.0294 0.02819 0.01982 -0.0612 0.0072 0.6835
9.000 1.0412 0.02930 0.02097 -0.0602 0.0028 0.6859
9.250 1.0542 0.03036 0.02208 -0.0593 0.0026 0.6887
9.500 1.0666 0.03148 0.02326 -0.0584 0.0023 0.6916
9.750 1.0801 0.03255 0.02438 -0.0576 0.0023 0.6946
10.000 1.0933 0.03366 0.02554 -0.0568 0.0022 0.6975
10.250 1.1061 0.03481 0.02677 -0.0561 0.0022 0.7006
10.500 1.1187 0.03601 0.02806 -0.0554 0.0021 0.7041
10.750 1.1312 0.03724 0.02936 -0.0547 0.0021 0.7080
11.250 1.1551 0.03986 0.03213 -0.0533 0.0020 0.7155
11.500 1.1668 0.04122 0.03358 -0.0527 0.0020 0.7197
11.750 1.1780 0.04266 0.03510 -0.0521 0.0019 0.7239
12.000 1.1890 0.04416 0.03668 -0.0516 0.0019 0.7281
12.250 1.1994 0.04572 0.03833 -0.0510 0.0018 0.7326
12.500 1.2092 0.04737 0.04009 -0.0505 0.0017 0.7376
12.750 1.2188 0.04907 0.04189 -0.0500 0.0017 0.7424
13.000 1.2277 0.05087 0.04380 -0.0495 0.0016 0.7475
13.250 1.2371 0.05266 0.04568 -0.0491 0.0016 0.7532
13.500 1.2455 0.05458 0.04771 -0.0488 0.0015 0.7588
13.750 1.2535 0.05656 0.04981 -0.0484 0.0015 0.7650
14.000 1.2607 0.05868 0.05204 -0.0481 0.0015 0.7713
14.250 1.2674 0.06089 0.05436 -0.0479 0.0014 0.7782
14.500 1.2735 0.06323 0.05682 -0.0477 0.0014 0.7855
14.750 1.2795 0.06560 0.05931 -0.0476 0.0014 0.7933
15.000 1.2834 0.06827 0.06213 -0.0476 0.0014 0.8014
15.250 1.2871 0.07101 0.06500 -0.0476 0.0014 0.8103
15.500 1.2901 0.07390 0.06803 -0.0477 0.0013 0.8200
15.750 1.2906 0.07716 0.07144 -0.0479 0.0013 0.8308
16.000 1.2919 0.08036 0.07479 -0.0482 0.0013 0.8437
16.250 1.2903 0.08394 0.07853 -0.0486 0.0013 0.8585
16.500 1.2870 0.08768 0.08245 -0.0489 0.0013 0.8789
16.750 1.2789 0.09061 0.08559 -0.0476 0.0013 0.9776
17.000 1.2735 0.09522 0.09033 -0.0489 0.0012 1.0000
17.250 1.2684 0.09988 0.09511 -0.0502 0.0012 1.0000
17.500 1.2645 0.10444 0.09979 -0.0518 0.0012 1.0000
17.750 1.2556 0.10993 0.10540 -0.0537 0.0012 1.0000
18.000 1.2465 0.11555 0.11115 -0.0559 0.0012 1.0000
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Polar data table (+)
Polar graphs
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