LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Reynolds number: 50,000 Max Cl/Cd: 32.4 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l188root-il-50000.txt Download as CSV file: xf-l188root-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED L-188 ROOT 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3666 0.11010 0.10255 -0.0257 1.0000 0.3486
-9.250 -0.3800 0.10847 0.10103 -0.0246 1.0000 0.3618
-9.000 -0.3846 0.10676 0.09939 -0.0229 1.0000 0.3770
-8.750 -0.3678 0.10320 0.09584 -0.0215 1.0000 0.3926
-8.500 -0.3565 0.09998 0.09264 -0.0201 1.0000 0.4057
-8.250 -0.3583 0.09758 0.09031 -0.0182 1.0000 0.4180
-8.000 -0.3714 0.09600 0.08884 -0.0154 1.0000 0.4313
-7.750 -0.6344 0.07385 0.06700 -0.0333 1.0000 0.1894
-7.500 -0.6804 0.06663 0.05919 -0.0327 1.0000 0.1691
-7.250 -0.6783 0.06284 0.05532 -0.0310 1.0000 0.1675
-7.000 -0.6781 0.05903 0.05132 -0.0294 1.0000 0.1654
-6.750 -0.6768 0.05510 0.04709 -0.0280 1.0000 0.1629
-6.500 -0.6727 0.05129 0.04285 -0.0267 1.0000 0.1610
-6.250 -0.6637 0.04820 0.03937 -0.0254 1.0000 0.1622
-6.000 -0.6515 0.04540 0.03612 -0.0242 1.0000 0.1645
-5.750 -0.6362 0.04275 0.03299 -0.0232 1.0000 0.1666
-5.500 -0.6186 0.04048 0.03012 -0.0223 1.0000 0.1701
-5.250 -0.5987 0.03853 0.02825 -0.0217 1.0000 0.1764
-5.000 -0.5776 0.03683 0.02618 -0.0210 1.0000 0.1829
-4.750 -0.5561 0.03518 0.02435 -0.0203 1.0000 0.1911
-4.500 -0.5339 0.03390 0.02284 -0.0197 1.0000 0.2012
-4.250 -0.5119 0.03262 0.02157 -0.0190 1.0000 0.2134
-4.000 -0.4892 0.03147 0.02040 -0.0183 1.0000 0.2282
-3.750 -0.4666 0.03044 0.01942 -0.0175 1.0000 0.2477
-3.500 -0.4437 0.02945 0.01852 -0.0168 1.0000 0.2745
-3.250 -0.4210 0.02832 0.01772 -0.0161 1.0000 0.3149
-3.000 -0.3988 0.02660 0.01698 -0.0155 1.0000 0.4123
-2.750 -0.3980 0.02622 0.01835 -0.0065 1.0000 0.6988
-2.500 -0.3986 0.02686 0.01908 0.0025 1.0000 0.7993
-2.250 -0.3930 0.02737 0.01957 0.0101 1.0000 0.8652
-2.000 -0.3291 0.02915 0.02101 0.0076 1.0000 0.9429
-1.750 -0.1457 0.03171 0.02276 -0.0207 1.0000 1.0000
-1.500 -0.1503 0.03131 0.02228 -0.0176 1.0000 1.0000
-1.250 -0.1552 0.03089 0.02178 -0.0145 1.0000 1.0000
-1.000 -0.1601 0.03045 0.02127 -0.0113 1.0000 1.0000
-0.750 -0.1648 0.02999 0.02074 -0.0080 1.0000 1.0000
-0.500 -0.1676 0.02958 0.02024 -0.0050 1.0000 1.0000
-0.250 -0.1648 0.02933 0.01988 -0.0028 1.0000 1.0000
0.000 -0.1544 0.02936 0.01977 -0.0018 1.0000 1.0000
0.250 -0.1393 0.02959 0.01985 -0.0016 1.0000 1.0000
0.500 -0.1216 0.02997 0.02008 -0.0016 1.0000 1.0000
0.750 -0.1027 0.03045 0.02043 -0.0018 1.0000 1.0000
1.000 -0.0832 0.03101 0.02085 -0.0021 1.0000 1.0000
1.250 -0.0634 0.03163 0.02137 -0.0024 1.0000 1.0000
1.500 -0.0435 0.03231 0.02195 -0.0027 1.0000 1.0000
1.750 -0.0237 0.03304 0.02259 -0.0030 1.0000 1.0000
2.000 -0.0039 0.03382 0.02330 -0.0034 1.0000 1.0000
2.250 0.0157 0.03466 0.02407 -0.0037 1.0000 1.0000
2.500 0.0351 0.03554 0.02490 -0.0040 1.0000 1.0000
2.750 0.0542 0.03647 0.02580 -0.0044 1.0000 1.0000
3.000 0.0730 0.03746 0.02676 -0.0047 1.0000 1.0000
3.250 0.0915 0.03850 0.02779 -0.0051 1.0000 1.0000
3.500 0.1096 0.03961 0.02889 -0.0054 1.0000 1.0000
3.750 0.2315 0.04372 0.03308 -0.0240 0.9327 1.0000
4.000 0.2902 0.04565 0.03507 -0.0303 0.9073 1.0000
4.250 0.3185 0.04652 0.03600 -0.0314 0.8844 1.0000
4.500 0.3615 0.04760 0.03717 -0.0345 0.8600 1.0000
4.750 0.4056 0.04850 0.03817 -0.0373 0.8350 1.0000
5.000 0.4446 0.04904 0.03883 -0.0390 0.8094 1.0000
5.250 0.4884 0.04931 0.03924 -0.0408 0.7836 1.0000
5.500 0.5376 0.04903 0.03913 -0.0426 0.7572 1.0000
5.750 0.5751 0.04864 0.03890 -0.0426 0.7298 1.0000
6.000 0.6433 0.04645 0.03699 -0.0446 0.7045 1.0000
6.250 0.6801 0.04498 0.03572 -0.0431 0.6751 1.0000
6.500 0.7401 0.04133 0.03237 -0.0421 0.6475 1.0000
6.750 0.8208 0.03503 0.02645 -0.0413 0.6159 1.0000
7.000 0.8791 0.02998 0.02151 -0.0383 0.5554 1.0000
7.250 0.9091 0.02806 0.01897 -0.0339 0.4564 1.0000
7.500 0.9257 0.02906 0.01908 -0.0306 0.3803 1.0000
7.750 0.9488 0.03082 0.02026 -0.0294 0.3284 1.0000
8.000 0.9773 0.03264 0.02172 -0.0293 0.2912 1.0000
8.250 1.0070 0.03452 0.02342 -0.0295 0.2638 1.0000
8.500 1.0357 0.03643 0.02523 -0.0296 0.2427 1.0000
8.750 1.0625 0.03843 0.02721 -0.0295 0.2259 1.0000
9.000 1.0865 0.04059 0.02946 -0.0290 0.2128 1.0000
9.250 1.1116 0.04291 0.03179 -0.0288 0.2016 1.0000
9.500 1.1294 0.04511 0.03420 -0.0276 0.1923 1.0000
9.750 1.1462 0.04779 0.03708 -0.0264 0.1850 1.0000
10.000 1.1554 0.05040 0.04005 -0.0242 0.1790 1.0000
10.250 1.1802 0.05331 0.04285 -0.0243 0.1721 1.0000
10.500 1.1738 0.05633 0.04642 -0.0205 0.1693 1.0000
10.750 1.1670 0.05966 0.05019 -0.0171 0.1669 1.0000
11.000 1.1579 0.06310 0.05397 -0.0138 0.1648 1.0000
11.250 1.1465 0.06661 0.05776 -0.0106 0.1629 1.0000
11.500 1.1276 0.07026 0.06166 -0.0070 0.1619 1.0000
11.750 1.0877 0.07504 0.06672 -0.0031 0.1634 1.0000
12.000 1.0369 0.08152 0.07345 -0.0012 0.1664 1.0000
12.250 0.9910 0.08930 0.08138 -0.0018 0.1693 1.0000
12.500 0.9571 0.09761 0.08977 -0.0039 0.1713 1.0000
12.750 0.9364 0.10565 0.09787 -0.0064 0.1725 1.0000
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Polar data table (+)
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