A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: A18 (smoothed) (a18sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.82 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a18sm-il-1000000.txt Download as CSV file: xf-a18sm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4108 0.09403 0.09238 -0.0285 1.0000 0.0138
-8.500 -0.4127 0.09103 0.08941 -0.0286 1.0000 0.0143
-8.250 -0.5126 0.02499 0.02240 -0.0921 0.9958 0.0092
-8.000 -0.4790 0.02133 0.01830 -0.0966 0.9951 0.0095
-7.750 -0.4455 0.01847 0.01504 -0.0998 0.9945 0.0098
-7.500 -0.4131 0.01669 0.01298 -0.1019 0.9934 0.0102
-7.250 -0.3808 0.01541 0.01148 -0.1035 0.9918 0.0107
-7.000 -0.3477 0.01446 0.01034 -0.1050 0.9904 0.0111
-6.750 -0.3143 0.01378 0.00953 -0.1065 0.9890 0.0113
-6.500 -0.2807 0.01196 0.00740 -0.1084 0.9879 0.0120
-6.250 -0.2466 0.01105 0.00636 -0.1101 0.9869 0.0128
-6.000 -0.2120 0.01055 0.00580 -0.1117 0.9859 0.0136
-5.750 -0.1770 0.01009 0.00527 -0.1134 0.9850 0.0147
-5.500 -0.1419 0.00982 0.00495 -0.1150 0.9843 0.0159
-5.250 -0.1066 0.00908 0.00413 -0.1168 0.9837 0.0187
-5.000 -0.0754 0.00881 0.00383 -0.1175 0.9809 0.0210
-4.750 -0.0438 0.00861 0.00360 -0.1183 0.9779 0.0224
-4.500 -0.0111 0.00810 0.00306 -0.1194 0.9754 0.0273
-4.250 0.0212 0.00791 0.00283 -0.1203 0.9728 0.0303
-4.000 0.0531 0.00758 0.00251 -0.1212 0.9700 0.0373
-3.750 0.0809 0.00739 0.00231 -0.1210 0.9639 0.0438
-3.500 0.1104 0.00719 0.00212 -0.1213 0.9591 0.0526
-3.250 0.1388 0.00698 0.00196 -0.1213 0.9530 0.0650
-3.000 0.1668 0.00682 0.00181 -0.1212 0.9461 0.0785
-2.750 0.1949 0.00667 0.00169 -0.1211 0.9387 0.0941
-2.500 0.2228 0.00654 0.00159 -0.1210 0.9307 0.1088
-2.250 0.2506 0.00642 0.00150 -0.1209 0.9214 0.1256
-2.000 0.2785 0.00632 0.00142 -0.1208 0.9120 0.1427
-1.750 0.3063 0.00624 0.00135 -0.1206 0.9017 0.1616
-1.500 0.3343 0.00615 0.00129 -0.1205 0.8900 0.1817
-1.000 0.3902 0.00601 0.00121 -0.1204 0.8649 0.2321
-0.750 0.4182 0.00595 0.00119 -0.1203 0.8511 0.2656
-0.500 0.4462 0.00589 0.00119 -0.1203 0.8366 0.3032
-0.250 0.4741 0.00585 0.00119 -0.1202 0.8213 0.3436
0.000 0.5020 0.00582 0.00121 -0.1202 0.8055 0.3857
0.250 0.5298 0.00577 0.00124 -0.1202 0.7891 0.4385
0.500 0.5577 0.00570 0.00128 -0.1202 0.7721 0.5070
0.750 0.5849 0.00548 0.00137 -0.1201 0.7480 0.6547
1.000 0.6056 0.00484 0.00135 -0.1183 0.7187 1.0000
1.250 0.6327 0.00503 0.00139 -0.1180 0.6894 1.0000
1.500 0.6602 0.00519 0.00145 -0.1179 0.6653 1.0000
1.750 0.6877 0.00535 0.00151 -0.1177 0.6447 1.0000
2.000 0.7154 0.00549 0.00158 -0.1177 0.6250 1.0000
2.250 0.7429 0.00566 0.00166 -0.1175 0.6050 1.0000
2.500 0.7704 0.00582 0.00176 -0.1174 0.5850 1.0000
2.750 0.7977 0.00601 0.00186 -0.1173 0.5624 1.0000
3.000 0.8248 0.00621 0.00197 -0.1171 0.5370 1.0000
3.250 0.8513 0.00650 0.00210 -0.1169 0.5018 1.0000
3.500 0.8779 0.00676 0.00225 -0.1166 0.4690 1.0000
3.750 0.9039 0.00711 0.00242 -0.1163 0.4247 1.0000
4.000 0.9288 0.00762 0.00266 -0.1159 0.3622 1.0000
4.250 0.9511 0.00850 0.00305 -0.1151 0.2615 1.0000
4.500 0.9742 0.00927 0.00346 -0.1145 0.1874 1.0000
4.750 0.9991 0.00977 0.00377 -0.1140 0.1482 1.0000
5.000 1.0241 0.01022 0.00407 -0.1136 0.1160 1.0000
5.250 1.0486 0.01074 0.00442 -0.1131 0.0835 1.0000
5.500 1.0728 0.01128 0.00480 -0.1125 0.0545 1.0000
5.750 1.0970 0.01181 0.00522 -0.1119 0.0352 1.0000
6.000 1.1215 0.01229 0.00566 -0.1113 0.0259 1.0000
6.250 1.1465 0.01268 0.00604 -0.1108 0.0216 1.0000
6.500 1.1705 0.01321 0.00660 -0.1101 0.0179 1.0000
6.750 1.1952 0.01360 0.00704 -0.1095 0.0163 1.0000
7.000 1.2191 0.01408 0.00753 -0.1088 0.0148 1.0000
7.250 1.2396 0.01502 0.00857 -0.1074 0.0129 1.0000
7.500 1.2639 0.01540 0.00898 -0.1068 0.0125 1.0000
7.750 1.2871 0.01589 0.00953 -0.1060 0.0119 1.0000
8.000 1.3096 0.01645 0.01014 -0.1051 0.0112 1.0000
8.250 1.3317 0.01704 0.01079 -0.1041 0.0107 1.0000
8.500 1.3536 0.01761 0.01139 -0.1032 0.0101 1.0000
8.750 1.3724 0.01852 0.01236 -0.1017 0.0094 1.0000
9.000 1.3850 0.02016 0.01416 -0.0991 0.0088 1.0000
9.250 1.4061 0.02071 0.01477 -0.0981 0.0086 1.0000
9.500 1.4260 0.02138 0.01552 -0.0968 0.0083 1.0000
9.750 1.4445 0.02216 0.01638 -0.0953 0.0080 1.0000
10.000 1.4621 0.02300 0.01732 -0.0937 0.0076 1.0000
10.250 1.4789 0.02387 0.01827 -0.0920 0.0073 1.0000
10.500 1.4952 0.02470 0.01917 -0.0903 0.0070 1.0000
10.750 1.5098 0.02559 0.02014 -0.0883 0.0068 1.0000
11.000 1.5214 0.02666 0.02129 -0.0859 0.0065 1.0000
11.250 1.5257 0.02821 0.02296 -0.0823 0.0063 1.0000
11.500 1.5159 0.03124 0.02625 -0.0768 0.0060 1.0000
11.750 1.5148 0.03340 0.02861 -0.0730 0.0058 1.0000
12.000 1.5236 0.03436 0.02968 -0.0707 0.0057 1.0000
12.250 1.5305 0.03559 0.03104 -0.0683 0.0056 1.0000
12.500 1.5342 0.03721 0.03279 -0.0658 0.0055 1.0000
12.750 1.5371 0.03896 0.03467 -0.0635 0.0053 1.0000
13.000 1.5366 0.04115 0.03701 -0.0612 0.0052 1.0000
13.250 1.5340 0.04369 0.03971 -0.0591 0.0051 1.0000
13.500 1.5294 0.04656 0.04275 -0.0574 0.0050 1.0000
13.750 1.5231 0.04983 0.04618 -0.0561 0.0049 1.0000
14.000 1.5152 0.05348 0.04999 -0.0552 0.0048 1.0000
14.250 1.5051 0.05766 0.05434 -0.0550 0.0048 1.0000
14.500 1.4920 0.06257 0.05943 -0.0554 0.0047 1.0000
14.750 1.4775 0.06797 0.06501 -0.0565 0.0047 1.0000
15.000 1.4614 0.07404 0.07125 -0.0584 0.0047 1.0000
15.250 1.4404 0.08141 0.07881 -0.0612 0.0047 1.0000
15.500 1.4185 0.08940 0.08697 -0.0648 0.0047 1.0000
15.750 1.3924 0.09884 0.09659 -0.0696 0.0047 1.0000
16.000 1.3648 0.10929 0.10722 -0.0753 0.0047 1.0000
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Polar data table (+)
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