A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: A18 (smoothed) (a18sm-il) Reynolds number: 200,000 Max Cl/Cd: 81.66 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a18sm-il-200000-n5.txt Download as CSV file: xf-a18sm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: A18 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4306 0.08633 0.08275 -0.0309 1.0000 0.0160
-8.000 -0.4392 0.08343 0.07992 -0.0301 1.0000 0.0160
-7.750 -0.4443 0.07981 0.07636 -0.0308 1.0000 0.0160
-7.500 -0.4480 0.07576 0.07237 -0.0325 1.0000 0.0159
-7.250 -0.4497 0.07101 0.06765 -0.0354 1.0000 0.0160
-6.750 -0.4202 0.03554 0.03142 -0.0740 0.9998 0.0164
-6.500 -0.3835 0.03104 0.02649 -0.0806 0.9978 0.0174
-6.250 -0.3457 0.02603 0.02075 -0.0864 0.9961 0.0182
-6.000 -0.3092 0.02282 0.01694 -0.0900 0.9945 0.0191
-5.750 -0.2744 0.02057 0.01419 -0.0924 0.9925 0.0204
-5.500 -0.2397 0.01892 0.01212 -0.0944 0.9900 0.0218
-5.250 -0.2049 0.01760 0.01059 -0.0964 0.9876 0.0240
-5.000 -0.1694 0.01699 0.00987 -0.0983 0.9851 0.0272
-4.750 -0.1333 0.01612 0.00878 -0.1002 0.9831 0.0301
-4.500 -0.1008 0.01530 0.00786 -0.1015 0.9790 0.0340
-4.250 -0.0663 0.01479 0.00725 -0.1030 0.9755 0.0392
-4.000 -0.0301 0.01412 0.00651 -0.1050 0.9728 0.0447
-3.750 0.0070 0.01370 0.00601 -0.1070 0.9705 0.0533
-3.500 0.0382 0.01327 0.00554 -0.1078 0.9647 0.0627
-3.250 0.0735 0.01290 0.00517 -0.1094 0.9609 0.0766
-3.000 0.1102 0.01255 0.00482 -0.1114 0.9580 0.0924
-2.750 0.1419 0.01226 0.00457 -0.1123 0.9522 0.1104
-2.500 0.1754 0.01199 0.00433 -0.1134 0.9471 0.1296
-2.250 0.2109 0.01172 0.00409 -0.1151 0.9433 0.1513
-2.000 0.2404 0.01151 0.00393 -0.1154 0.9351 0.1726
-1.750 0.2747 0.01126 0.00373 -0.1167 0.9300 0.1982
-1.500 0.3046 0.01106 0.00361 -0.1171 0.9213 0.2259
-1.250 0.3381 0.01082 0.00346 -0.1182 0.9151 0.2595
-1.000 0.3677 0.01063 0.00337 -0.1185 0.9052 0.2965
-0.750 0.3984 0.01043 0.00329 -0.1190 0.8959 0.3397
-0.500 0.4296 0.01020 0.00320 -0.1196 0.8867 0.3898
-0.250 0.4588 0.00998 0.00315 -0.1197 0.8753 0.4497
0.000 0.4872 0.00970 0.00313 -0.1197 0.8633 0.5365
0.250 0.5117 0.00911 0.00313 -0.1186 0.8507 0.7334
0.500 0.5372 0.00867 0.00294 -0.1174 0.8369 1.0000
0.750 0.5659 0.00872 0.00291 -0.1173 0.8227 1.0000
1.000 0.5943 0.00879 0.00289 -0.1171 0.8081 1.0000
1.250 0.6224 0.00887 0.00290 -0.1170 0.7928 1.0000
1.500 0.6503 0.00898 0.00295 -0.1167 0.7773 1.0000
1.750 0.6780 0.00910 0.00300 -0.1165 0.7614 1.0000
2.000 0.7055 0.00924 0.00308 -0.1162 0.7454 1.0000
2.250 0.7323 0.00940 0.00316 -0.1157 0.7233 1.0000
2.500 0.7581 0.00961 0.00325 -0.1150 0.6927 1.0000
2.750 0.7836 0.00987 0.00334 -0.1143 0.6606 1.0000
3.000 0.8097 0.01010 0.00349 -0.1137 0.6355 1.0000
3.250 0.8359 0.01033 0.00367 -0.1133 0.6134 1.0000
3.500 0.8619 0.01059 0.00389 -0.1127 0.5901 1.0000
3.750 0.8876 0.01087 0.00410 -0.1122 0.5646 1.0000
4.000 0.9126 0.01118 0.00434 -0.1115 0.5344 1.0000
4.250 0.9367 0.01158 0.00460 -0.1107 0.4941 1.0000
4.500 0.9592 0.01211 0.00489 -0.1096 0.4362 1.0000
4.750 0.9796 0.01287 0.00530 -0.1083 0.3533 1.0000
5.000 0.9978 0.01399 0.00589 -0.1069 0.2535 1.0000
5.250 1.0177 0.01500 0.00654 -0.1058 0.1863 1.0000
5.500 1.0390 0.01584 0.00715 -0.1049 0.1404 1.0000
5.750 1.0606 0.01664 0.00780 -0.1040 0.1024 1.0000
6.000 1.0814 0.01752 0.00849 -0.1029 0.0695 1.0000
6.250 1.1025 0.01835 0.00923 -0.1019 0.0496 1.0000
6.500 1.1237 0.01916 0.01002 -0.1008 0.0387 1.0000
6.750 1.1446 0.01997 0.01087 -0.0996 0.0324 1.0000
7.000 1.1651 0.02082 0.01179 -0.0984 0.0283 1.0000
7.250 1.1833 0.02192 0.01299 -0.0968 0.0255 1.0000
7.500 1.2029 0.02281 0.01401 -0.0954 0.0234 1.0000
7.750 1.2221 0.02369 0.01497 -0.0940 0.0211 1.0000
8.000 1.2393 0.02478 0.01612 -0.0924 0.0194 1.0000
8.250 1.2533 0.02631 0.01773 -0.0903 0.0183 1.0000
8.500 1.2702 0.02752 0.01909 -0.0885 0.0176 1.0000
8.750 1.2864 0.02888 0.02064 -0.0867 0.0168 1.0000
9.000 1.3023 0.03036 0.02228 -0.0848 0.0161 1.0000
9.250 1.3179 0.03179 0.02385 -0.0831 0.0152 1.0000
9.500 1.3328 0.03305 0.02522 -0.0813 0.0143 1.0000
9.750 1.3456 0.03438 0.02665 -0.0794 0.0136 1.0000
10.000 1.3550 0.03680 0.02920 -0.0771 0.0128 1.0000
10.250 1.3659 0.03866 0.03132 -0.0748 0.0126 1.0000
10.500 1.3730 0.04072 0.03367 -0.0720 0.0122 1.0000
10.750 1.3769 0.04303 0.03631 -0.0690 0.0119 1.0000
11.000 1.3775 0.04560 0.03918 -0.0658 0.0117 1.0000
11.250 1.3746 0.04841 0.04231 -0.0626 0.0114 1.0000
11.500 1.3683 0.05150 0.04571 -0.0595 0.0112 1.0000
11.750 1.3593 0.05486 0.04936 -0.0567 0.0111 1.0000
12.000 1.3482 0.05848 0.05327 -0.0545 0.0109 1.0000
12.250 1.3351 0.06250 0.05757 -0.0531 0.0107 1.0000
12.500 1.3196 0.06710 0.06243 -0.0524 0.0106 1.0000
12.750 1.3032 0.07215 0.06773 -0.0527 0.0105 1.0000
13.000 1.2838 0.07815 0.07397 -0.0541 0.0105 1.0000
13.250 1.2615 0.08523 0.08130 -0.0568 0.0105 1.0000
13.500 1.2363 0.09364 0.08995 -0.0611 0.0106 1.0000
13.750 1.2077 0.10383 0.10036 -0.0671 0.0108 1.0000
14.000 1.1772 0.11603 0.11277 -0.0751 0.0112 1.0000
14.250 1.1440 0.13147 0.12834 -0.0853 0.0116 1.0000
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Polar data table (+)
Polar graphs
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