A18 (original) (a18-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: A18 (original) (a18-il) Reynolds number: 100,000 Max Cl/Cd: 63.57 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a18-il-100000-n5.txt Download as CSV file: xf-a18-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: A18 (original)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4152 0.09313 0.08816 -0.0300 1.0000 0.0286
-9.000 -0.4198 0.08991 0.08502 -0.0301 1.0000 0.0286
-8.750 -0.4263 0.08677 0.08197 -0.0300 1.0000 0.0286
-8.500 -0.4291 0.08301 0.07829 -0.0314 1.0000 0.0287
-8.250 -0.4307 0.07885 0.07420 -0.0336 1.0000 0.0288
-8.000 -0.4302 0.07409 0.06949 -0.0369 1.0000 0.0291
-7.750 -0.4264 0.06779 0.06322 -0.0427 1.0000 0.0298
-7.500 -0.4140 0.05704 0.05239 -0.0546 1.0000 0.0307
-7.250 -0.3984 0.05493 0.05026 -0.0562 1.0000 0.0327
-7.000 -0.3732 0.04704 0.04212 -0.0648 1.0000 0.0346
-6.750 -0.3239 0.03067 0.02419 -0.0827 1.0000 0.0410
-6.500 -0.3032 0.03073 0.02429 -0.0819 1.0000 0.0454
-6.250 -0.2712 0.02698 0.01961 -0.0849 1.0000 0.0531
-6.000 -0.2490 0.02664 0.01927 -0.0845 1.0000 0.0586
-5.750 -0.2208 0.02517 0.01711 -0.0853 1.0000 0.0661
-5.500 -0.1945 0.02368 0.01545 -0.0858 1.0000 0.0693
-5.250 -0.1688 0.02283 0.01440 -0.0859 1.0000 0.0730
-5.000 -0.1367 0.02195 0.01313 -0.0872 0.9983 0.0783
-4.750 -0.0972 0.02080 0.01161 -0.0897 0.9950 0.0808
-4.500 -0.0597 0.01986 0.01060 -0.0920 0.9906 0.0838
-4.250 -0.0211 0.01917 0.00978 -0.0944 0.9867 0.0877
-4.000 0.0151 0.01858 0.00904 -0.0962 0.9816 0.0923
-3.750 0.0529 0.01808 0.00853 -0.0985 0.9773 0.0994
-3.500 0.0883 0.01764 0.00799 -0.1002 0.9713 0.1073
-3.250 0.1259 0.01717 0.00756 -0.1024 0.9666 0.1165
-3.000 0.1605 0.01677 0.00718 -0.1039 0.9604 0.1307
-2.750 0.1967 0.01639 0.00689 -0.1058 0.9549 0.1586
-2.500 0.2324 0.01607 0.00671 -0.1076 0.9496 0.1988
-2.250 0.2663 0.01581 0.00651 -0.1089 0.9427 0.2403
-2.000 0.3047 0.01544 0.00636 -0.1112 0.9382 0.2939
-1.750 0.3362 0.01519 0.00633 -0.1120 0.9291 0.3738
-1.500 0.3732 0.01470 0.00618 -0.1139 0.9237 0.4644
-1.250 0.4014 0.01416 0.00617 -0.1138 0.9141 0.6141
-1.000 0.4255 0.01330 0.00590 -0.1121 0.9043 1.0000
-0.750 0.4599 0.01327 0.00575 -0.1132 0.8964 1.0000
-0.500 0.4909 0.01328 0.00566 -0.1137 0.8855 1.0000
-0.250 0.5229 0.01326 0.00557 -0.1144 0.8749 1.0000
0.000 0.5555 0.01324 0.00550 -0.1151 0.8648 1.0000
0.250 0.5872 0.01323 0.00544 -0.1156 0.8535 1.0000
0.500 0.6172 0.01326 0.00547 -0.1158 0.8408 1.0000
0.750 0.6473 0.01330 0.00549 -0.1160 0.8279 1.0000
1.000 0.6773 0.01331 0.00549 -0.1161 0.8130 1.0000
1.250 0.7071 0.01332 0.00549 -0.1161 0.7951 1.0000
1.500 0.7352 0.01337 0.00553 -0.1157 0.7739 1.0000
1.750 0.7638 0.01344 0.00556 -0.1154 0.7533 1.0000
2.000 0.7912 0.01357 0.00571 -0.1149 0.7323 1.0000
2.250 0.8185 0.01373 0.00587 -0.1145 0.7115 1.0000
2.500 0.8454 0.01391 0.00607 -0.1140 0.6903 1.0000
2.750 0.8718 0.01412 0.00629 -0.1135 0.6671 1.0000
3.000 0.8977 0.01436 0.00657 -0.1128 0.6422 1.0000
3.250 0.9233 0.01462 0.00684 -0.1121 0.6155 1.0000
3.500 0.9484 0.01492 0.00713 -0.1113 0.5864 1.0000
3.750 0.9726 0.01530 0.00745 -0.1103 0.5535 1.0000
4.000 0.9954 0.01577 0.00786 -0.1091 0.5097 1.0000
4.250 1.0168 0.01629 0.00828 -0.1077 0.4445 1.0000
4.500 1.0359 0.01712 0.00878 -0.1060 0.3842 1.0000
4.750 1.0492 0.01861 0.00950 -0.1038 0.2509 1.0000
5.000 1.0649 0.02010 0.01052 -0.1023 0.1831 1.0000
5.250 1.0841 0.02118 0.01146 -0.1011 0.1338 1.0000
5.500 1.1005 0.02260 0.01248 -0.0996 0.0710 1.0000
5.750 1.1157 0.02423 0.01394 -0.0976 0.0445 1.0000
6.000 1.1326 0.02563 0.01537 -0.0958 0.0347 1.0000
6.250 1.1492 0.02699 0.01681 -0.0941 0.0295 1.0000
6.500 1.1656 0.02837 0.01835 -0.0922 0.0268 1.0000
6.750 1.1803 0.02992 0.02000 -0.0903 0.0248 1.0000
7.000 1.1938 0.03172 0.02191 -0.0882 0.0230 1.0000
7.250 1.2102 0.03332 0.02380 -0.0864 0.0213 1.0000
7.500 1.2263 0.03526 0.02594 -0.0846 0.0202 1.0000
7.750 1.2432 0.03745 0.02835 -0.0830 0.0194 1.0000
8.000 1.2603 0.03989 0.03104 -0.0814 0.0187 1.0000
8.250 1.2757 0.04248 0.03393 -0.0797 0.0180 1.0000
8.500 1.2876 0.04497 0.03672 -0.0778 0.0171 1.0000
8.750 1.2958 0.04748 0.03948 -0.0757 0.0163 1.0000
9.000 1.3000 0.05036 0.04263 -0.0732 0.0156 1.0000
9.250 1.2991 0.05378 0.04637 -0.0703 0.0151 1.0000
9.500 1.2922 0.05717 0.05010 -0.0667 0.0149 1.0000
9.750 1.2820 0.06065 0.05390 -0.0632 0.0148 1.0000
10.000 1.2694 0.06432 0.05787 -0.0602 0.0148 1.0000
10.250 1.2548 0.06827 0.06212 -0.0579 0.0148 1.0000
10.500 1.2390 0.07252 0.06664 -0.0565 0.0148 1.0000
10.750 1.2217 0.07726 0.07165 -0.0561 0.0148 1.0000
11.000 1.2039 0.08248 0.07711 -0.0568 0.0148 1.0000
11.250 1.1856 0.08831 0.08318 -0.0586 0.0149 1.0000
11.500 1.1661 0.09501 0.09010 -0.0617 0.0150 1.0000
11.750 1.1459 0.10279 0.09809 -0.0663 0.0151 1.0000
12.000 1.1230 0.11244 0.10796 -0.0726 0.0154 1.0000
12.250 1.0913 0.12734 0.12306 -0.0829 0.0160 1.0000
|
Polar data table (+)
Polar graphs
<< Back to A18 (original) (a18-il)