FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: FX 38-153 AIRFOIL (fx38153-il) Reynolds number: 50,000 Max Cl/Cd: 31.22 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx38153-il-50000.txt Download as CSV file: xf-fx38153-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.7425 0.07649 0.07019 -0.0221 1.0001 0.1784
-7.000 -0.7503 0.06861 0.06141 -0.0218 1.0001 0.1308
-6.750 -0.7439 0.06348 0.05582 -0.0204 1.0001 0.1158
-6.500 -0.7359 0.05911 0.05066 -0.0187 1.0001 0.1038
-6.250 -0.7211 0.05525 0.04662 -0.0176 1.0001 0.0995
-6.000 -0.7052 0.05152 0.04212 -0.0163 1.0001 0.0937
-5.750 -0.6855 0.04910 0.03898 -0.0150 1.0001 0.0914
-5.500 -0.6646 0.04647 0.03598 -0.0141 1.0001 0.0913
-5.250 -0.6423 0.04420 0.03332 -0.0130 1.0001 0.0916
-5.000 -0.6193 0.04188 0.03076 -0.0119 1.0001 0.0925
-4.750 -0.5961 0.03985 0.02860 -0.0107 1.0001 0.0939
-4.500 -0.5727 0.03825 0.02694 -0.0091 1.0001 0.0964
-4.250 -0.5489 0.03705 0.02564 -0.0071 1.0001 0.1008
-4.000 -0.5252 0.03608 0.02469 -0.0046 1.0001 0.1090
-3.750 -0.1323 0.04384 0.03457 -0.0352 1.0001 0.9999
-3.500 -0.1268 0.04326 0.03383 -0.0332 1.0001 0.9999
-3.250 -0.1210 0.04275 0.03316 -0.0313 1.0001 0.9999
-3.000 -0.1150 0.04229 0.03256 -0.0293 1.0001 0.9999
-2.750 -0.1089 0.04190 0.03203 -0.0272 1.0001 0.9999
-2.500 -0.1026 0.04156 0.03156 -0.0251 1.0001 0.9999
-2.250 -0.0962 0.04127 0.03116 -0.0230 1.0001 0.9999
-2.000 -0.0898 0.04102 0.03081 -0.0209 1.0001 0.9999
-1.750 -0.0833 0.04083 0.03051 -0.0187 1.0001 0.9999
-1.500 -0.0768 0.04067 0.03025 -0.0165 1.0001 0.9999
-1.250 -0.0704 0.04056 0.03006 -0.0144 1.0001 0.9999
-1.000 -0.0640 0.04049 0.02991 -0.0122 1.0001 0.9999
-0.750 -0.0577 0.04046 0.02981 -0.0099 1.0001 0.9999
-0.500 -0.0515 0.04047 0.02976 -0.0077 1.0001 0.9999
-0.250 -0.0454 0.04052 0.02974 -0.0055 1.0001 0.9999
0.000 -0.0395 0.04060 0.02978 -0.0033 1.0001 0.9999
0.250 -0.0338 0.04073 0.02986 -0.0011 1.0001 0.9999
0.500 -0.0283 0.04089 0.02999 0.0011 1.0001 0.9999
0.750 -0.0230 0.04108 0.03015 0.0033 1.0001 0.9999
1.000 -0.0179 0.04131 0.03035 0.0055 1.0001 0.9999
1.250 -0.0131 0.04158 0.03060 0.0077 1.0001 0.9999
1.500 -0.0085 0.04188 0.03089 0.0098 1.0001 0.9999
1.750 -0.0041 0.04221 0.03122 0.0119 1.0001 0.9999
2.000 0.0000 0.04258 0.03159 0.0140 1.0001 0.9999
2.250 0.0040 0.04298 0.03199 0.0160 1.0001 0.9999
2.500 0.0077 0.04341 0.03243 0.0180 1.0001 0.9999
2.750 0.0112 0.04388 0.03291 0.0199 1.0001 0.9999
3.000 0.0146 0.04437 0.03343 0.0218 1.0001 0.9999
3.250 0.0179 0.04490 0.03398 0.0235 1.0001 0.9999
3.500 0.1710 0.04917 0.03830 -0.0017 0.9275 0.9999
3.750 0.2100 0.04996 0.03915 -0.0052 0.9018 0.9999
4.000 0.2504 0.05076 0.03999 -0.0088 0.8809 0.9999
4.250 0.2761 0.05126 0.04056 -0.0098 0.8613 0.9999
4.500 0.3009 0.05168 0.04105 -0.0106 0.8417 0.9999
4.750 0.3377 0.05202 0.04149 -0.0129 0.8225 0.9999
5.000 0.3659 0.05220 0.04176 -0.0137 0.8026 0.9999
5.250 0.3890 0.05236 0.04200 -0.0136 0.7827 0.9999
5.500 0.4196 0.05243 0.04221 -0.0145 0.7644 0.9999
5.750 0.4618 0.05203 0.04194 -0.0164 0.7460 0.9999
6.000 0.4807 0.05191 0.04192 -0.0151 0.7251 0.9999
6.250 0.5087 0.05147 0.04164 -0.0147 0.7048 0.9999
6.500 0.5441 0.05080 0.04113 -0.0151 0.6866 0.9999
6.750 0.5906 0.04937 0.03993 -0.0162 0.6688 0.9999
7.000 0.6157 0.04850 0.03921 -0.0146 0.6473 0.9999
7.250 0.6585 0.04641 0.03734 -0.0142 0.6267 0.9999
7.500 0.7293 0.04259 0.03385 -0.0162 0.6091 0.9999
7.750 0.9013 0.03456 0.02629 -0.0301 0.5676 0.9999
8.000 0.9968 0.03286 0.02452 -0.0384 0.5047 0.9999
8.250 1.0405 0.03333 0.02482 -0.0403 0.4592 0.9999
8.500 1.0547 0.03409 0.02548 -0.0376 0.4270 0.9999
8.750 1.0690 0.03482 0.02606 -0.0350 0.3966 0.9999
9.000 1.0637 0.03562 0.02689 -0.0294 0.3756 0.9999
9.250 1.0821 0.03651 0.02763 -0.0277 0.3496 0.9999
9.500 1.0849 0.03760 0.02881 -0.0237 0.3310 0.9999
9.750 1.0904 0.03878 0.03006 -0.0202 0.3126 0.9999
10.000 1.1007 0.03988 0.03115 -0.0175 0.2927 0.9999
10.250 1.1130 0.04092 0.03206 -0.0153 0.2712 0.9999
10.500 1.1109 0.04195 0.03316 -0.0111 0.2543 0.9999
10.750 1.1150 0.04332 0.03465 -0.0080 0.2372 0.9999
11.000 1.1235 0.04511 0.03654 -0.0058 0.2202 0.9999
11.250 1.1302 0.04696 0.03850 -0.0035 0.2040 0.9999
11.500 1.1343 0.04871 0.04032 -0.0010 0.1884 0.9999
11.750 1.1368 0.05055 0.04224 0.0015 0.1741 0.9999
12.000 1.1423 0.05300 0.04481 0.0034 0.1618 0.9999
12.250 1.1525 0.05550 0.04735 0.0046 0.1499 0.9999
12.500 1.1371 0.05865 0.05095 0.0083 0.1450 0.9999
12.750 1.1524 0.06181 0.05416 0.0087 0.1363 0.9999
13.000 1.1281 0.06559 0.05838 0.0123 0.1347 0.9999
13.250 1.1021 0.06984 0.06300 0.0151 0.1336 0.9999
13.500 1.0729 0.07471 0.06819 0.0170 0.1332 0.9999
13.750 1.0397 0.08041 0.07415 0.0177 0.1337 0.9999
14.000 1.0034 0.08718 0.08115 0.0171 0.1348 0.9999
14.250 0.9671 0.09506 0.08919 0.0148 0.1361 0.9999
14.500 0.9325 0.10409 0.09831 0.0110 0.1372 0.9999
14.750 0.7675 0.14733 0.14117 -0.0171 0.1821 0.9999
15.000 0.7588 0.15470 0.14852 -0.0214 0.1824 0.9999
15.250 0.7558 0.16088 0.15469 -0.0248 0.1803 0.9999
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