FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 38-153 AIRFOIL (fx38153-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.27 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx38153-il-1000000-n5.txt Download as CSV file: xf-fx38153-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 38-153 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5763 0.05683 0.05432 -0.1183 0.9527 0.0034
-13.750 -0.6015 0.05001 0.04726 -0.1216 0.9501 0.0034
-13.500 -0.6198 0.04507 0.04211 -0.1228 0.9474 0.0034
-13.250 -0.6324 0.04126 0.03810 -0.1229 0.9449 0.0034
-13.000 -0.6409 0.03812 0.03477 -0.1223 0.9424 0.0034
-12.750 -0.6456 0.03546 0.03191 -0.1214 0.9398 0.0034
-12.500 -0.6468 0.03314 0.02942 -0.1204 0.9378 0.0034
-12.250 -0.6451 0.03109 0.02721 -0.1193 0.9358 0.0035
-12.000 -0.6406 0.02928 0.02524 -0.1182 0.9338 0.0035
-11.750 -0.6337 0.02766 0.02346 -0.1170 0.9318 0.0035
-11.500 -0.6245 0.02621 0.02186 -0.1158 0.9300 0.0036
-11.250 -0.6131 0.02489 0.02040 -0.1148 0.9282 0.0036
-11.000 -0.6001 0.02368 0.01904 -0.1138 0.9264 0.0037
-10.750 -0.5851 0.02260 0.01783 -0.1129 0.9245 0.0038
-10.500 -0.5687 0.02159 0.01670 -0.1121 0.9232 0.0039
-10.250 -0.5512 0.02065 0.01566 -0.1114 0.9218 0.0039
-10.000 -0.5327 0.01978 0.01469 -0.1107 0.9201 0.0040
-9.750 -0.5133 0.01898 0.01380 -0.1101 0.9185 0.0041
-9.500 -0.4933 0.01823 0.01296 -0.1096 0.9170 0.0042
-9.250 -0.4726 0.01756 0.01221 -0.1090 0.9155 0.0043
-9.000 -0.4515 0.01693 0.01150 -0.1085 0.9140 0.0044
-8.750 -0.4300 0.01634 0.01084 -0.1081 0.9126 0.0045
-8.500 -0.4080 0.01579 0.01023 -0.1077 0.9113 0.0046
-8.250 -0.3856 0.01528 0.00966 -0.1073 0.9100 0.0047
-8.000 -0.3635 0.01481 0.00915 -0.1069 0.9087 0.0047
-7.750 -0.3424 0.01438 0.00868 -0.1063 0.9072 0.0048
-7.500 -0.3216 0.01400 0.00826 -0.1055 0.9055 0.0048
-7.250 -0.3005 0.01363 0.00786 -0.1049 0.9038 0.0049
-7.000 -0.2783 0.01325 0.00746 -0.1044 0.9023 0.0049
-6.750 -0.2569 0.01273 0.00691 -0.1038 0.9006 0.0050
-6.500 -0.2349 0.01224 0.00637 -0.1034 0.8989 0.0051
-6.250 -0.2119 0.01179 0.00589 -0.1031 0.8973 0.0053
-6.000 -0.1873 0.01142 0.00550 -0.1031 0.8958 0.0055
-5.750 -0.1616 0.01112 0.00517 -0.1032 0.8944 0.0056
-5.500 -0.1374 0.01087 0.00490 -0.1030 0.8930 0.0056
-5.250 -0.1132 0.01064 0.00467 -0.1027 0.8912 0.0056
-5.000 -0.0884 0.01041 0.00444 -0.1025 0.8893 0.0057
-4.750 -0.0629 0.01021 0.00422 -0.1025 0.8875 0.0057
-4.500 -0.0367 0.00999 0.00399 -0.1025 0.8851 0.0058
-4.250 -0.0096 0.00978 0.00376 -0.1028 0.8827 0.0059
-4.000 0.0191 0.00957 0.00352 -0.1033 0.8799 0.0060
-3.750 0.0438 0.00941 0.00336 -0.1029 0.8763 0.0061
-3.500 0.0691 0.00924 0.00320 -0.1027 0.8722 0.0063
-3.250 0.0960 0.00908 0.00303 -0.1028 0.8689 0.0066
-3.000 0.1247 0.00892 0.00287 -0.1033 0.8659 0.0076
-2.750 0.1500 0.00878 0.00276 -0.1031 0.8606 0.0145
-2.500 0.1763 0.00862 0.00259 -0.1030 0.8527 0.0175
-2.250 0.2022 0.00850 0.00246 -0.1028 0.8438 0.0190
-2.000 0.2287 0.00837 0.00231 -0.1028 0.8331 0.0218
-1.750 0.2540 0.00822 0.00217 -0.1025 0.8191 0.0439
-1.500 0.2779 0.00798 0.00202 -0.1021 0.7984 0.1005
-1.250 0.3002 0.00781 0.00190 -0.1013 0.7724 0.1551
-1.000 0.3213 0.00752 0.00178 -0.1006 0.7415 0.2567
-0.750 0.3484 0.00681 0.00157 -0.1019 0.7113 0.4501
-0.500 0.3749 0.00651 0.00151 -0.1027 0.6592 0.5890
-0.250 0.3945 0.00677 0.00173 -0.1017 0.5851 0.6803
0.000 0.4114 0.00724 0.00200 -0.0997 0.5196 0.7108
0.250 0.4299 0.00765 0.00224 -0.0981 0.4694 0.7291
0.500 0.4515 0.00798 0.00238 -0.0971 0.4309 0.7379
0.750 0.4739 0.00825 0.00253 -0.0963 0.4018 0.7412
1.000 0.4970 0.00852 0.00269 -0.0956 0.3722 0.7451
1.250 0.5205 0.00882 0.00285 -0.0950 0.3444 0.7499
1.500 0.5445 0.00912 0.00303 -0.0945 0.3167 0.7558
1.750 0.5662 0.00950 0.00328 -0.0935 0.2848 0.7615
2.000 0.5868 0.01000 0.00356 -0.0925 0.2352 0.7654
2.250 0.6081 0.01050 0.00382 -0.0916 0.1871 0.7682
2.500 0.6318 0.01085 0.00403 -0.0912 0.1598 0.7697
2.750 0.6531 0.01130 0.00429 -0.0903 0.1220 0.7711
3.000 0.6753 0.01170 0.00456 -0.0895 0.0905 0.7723
3.250 0.7000 0.01194 0.00475 -0.0892 0.0821 0.7733
3.500 0.7228 0.01230 0.00501 -0.0886 0.0595 0.7743
3.750 0.7472 0.01255 0.00523 -0.0883 0.0531 0.7753
4.000 0.7718 0.01278 0.00544 -0.0880 0.0485 0.7764
4.250 0.7955 0.01308 0.00569 -0.0876 0.0361 0.7776
4.500 0.8193 0.01337 0.00595 -0.0872 0.0310 0.7789
4.750 0.8435 0.01363 0.00619 -0.0868 0.0288 0.7801
5.000 0.8676 0.01388 0.00644 -0.0865 0.0266 0.7812
5.250 0.8919 0.01412 0.00668 -0.0862 0.0254 0.7822
5.500 0.9159 0.01438 0.00694 -0.0858 0.0233 0.7831
5.750 0.9379 0.01477 0.00729 -0.0852 0.0148 0.7840
6.000 0.9611 0.01508 0.00759 -0.0847 0.0130 0.7848
6.250 0.9842 0.01537 0.00789 -0.0842 0.0127 0.7859
6.500 1.0067 0.01568 0.00822 -0.0836 0.0124 0.7868
6.750 1.0289 0.01601 0.00858 -0.0830 0.0122 0.7877
7.000 1.0508 0.01635 0.00894 -0.0823 0.0121 0.7885
7.250 1.0724 0.01671 0.00933 -0.0816 0.0119 0.7894
7.500 1.0935 0.01712 0.00977 -0.0808 0.0115 0.7903
7.750 1.1143 0.01753 0.01021 -0.0800 0.0111 0.7911
8.000 1.1343 0.01799 0.01070 -0.0790 0.0107 0.7920
8.250 1.1543 0.01845 0.01119 -0.0781 0.0105 0.7930
8.500 1.1741 0.01893 0.01171 -0.0771 0.0104 0.7939
8.750 1.1932 0.01945 0.01227 -0.0761 0.0101 0.7948
9.000 1.2124 0.01995 0.01280 -0.0751 0.0100 0.7958
9.250 1.2319 0.02042 0.01330 -0.0742 0.0098 0.7968
9.500 1.2509 0.02093 0.01384 -0.0733 0.0096 0.7979
9.750 1.2696 0.02146 0.01441 -0.0723 0.0094 0.7988
10.000 1.2879 0.02201 0.01500 -0.0713 0.0091 0.7996
10.250 1.3053 0.02262 0.01564 -0.0701 0.0088 0.8003
10.500 1.3226 0.02322 0.01629 -0.0690 0.0086 0.8011
10.750 1.3394 0.02385 0.01697 -0.0678 0.0083 0.8020
11.000 1.3555 0.02453 0.01769 -0.0666 0.0080 0.8030
11.250 1.3704 0.02530 0.01850 -0.0652 0.0077 0.8039
11.500 1.3844 0.02612 0.01938 -0.0637 0.0074 0.8047
11.750 1.4015 0.02671 0.02002 -0.0627 0.0072 0.8056
12.000 1.4178 0.02736 0.02072 -0.0617 0.0069 0.8065
12.250 1.4338 0.02806 0.02146 -0.0606 0.0064 0.8075
12.500 1.4482 0.02886 0.02234 -0.0593 0.0051 0.8084
12.750 1.4607 0.02979 0.02319 -0.0580 0.0024 0.8095
13.000 1.4701 0.03098 0.02444 -0.0562 0.0021 0.8106
13.250 1.4793 0.03221 0.02574 -0.0545 0.0019 0.8117
13.500 1.4881 0.03350 0.02711 -0.0528 0.0017 0.8127
13.750 1.4973 0.03479 0.02847 -0.0513 0.0016 0.8136
14.000 1.5054 0.03618 0.02994 -0.0498 0.0015 0.8144
14.250 1.5132 0.03764 0.03148 -0.0483 0.0015 0.8152
14.500 1.5198 0.03924 0.03317 -0.0469 0.0014 0.8159
14.750 1.5258 0.04094 0.03496 -0.0455 0.0014 0.8168
15.000 1.5309 0.04277 0.03689 -0.0442 0.0013 0.8178
15.250 1.5352 0.04472 0.03894 -0.0430 0.0013 0.8189
15.500 1.5384 0.04683 0.04115 -0.0418 0.0013 0.8200
15.750 1.5406 0.04913 0.04355 -0.0408 0.0012 0.8211
16.000 1.5415 0.05165 0.04619 -0.0399 0.0012 0.8220
16.250 1.5413 0.05438 0.04903 -0.0392 0.0012 0.8230
16.500 1.5397 0.05736 0.05212 -0.0386 0.0011 0.8239
16.750 1.5369 0.06059 0.05547 -0.0383 0.0011 0.8248
17.000 1.5340 0.06395 0.05894 -0.0382 0.0011 0.8257
17.250 1.5290 0.06771 0.06282 -0.0384 0.0011 0.8266
17.500 1.5225 0.07179 0.06703 -0.0388 0.0011 0.8274
17.750 1.5144 0.07619 0.07156 -0.0395 0.0011 0.8282
18.000 1.5041 0.08104 0.07654 -0.0406 0.0010 0.8290
18.250 1.4925 0.08625 0.08188 -0.0419 0.0010 0.8297
18.500 1.4793 0.09183 0.08760 -0.0437 0.0010 0.8303
18.750 1.4658 0.09761 0.09351 -0.0457 0.0010 0.8309
19.000 1.4488 0.10405 0.10009 -0.0482 0.0010 0.8315
19.250 1.4314 0.11072 0.10689 -0.0510 0.0010 0.8319
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