FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-145 AIRFOIL (fx63145-il) Reynolds number: 200,000 Max Cl/Cd: 59.1 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63145-il-200000-n5.txt Download as CSV file: xf-fx63145-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-145 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1005 0.10053 0.09635 -0.0739 0.7525 0.0307
-11.000 -0.1088 0.09480 0.09055 -0.0784 0.7354 0.0320
-10.500 -0.1647 0.09886 0.09452 -0.0767 0.7708 0.0298
-9.000 -0.1776 0.06078 0.05601 -0.1021 0.6736 0.0167
-8.750 -0.1814 0.05709 0.05225 -0.1045 0.6611 0.0164
-8.500 -0.1928 0.05281 0.04788 -0.1075 0.6517 0.0161
-8.250 -0.1701 0.03599 0.03113 -0.1035 0.6258 0.0151
-7.750 -0.2271 0.03932 0.03338 -0.1126 0.6257 0.0128
-7.500 -0.2165 0.03680 0.03063 -0.1129 0.6143 0.0126
-7.250 -0.2028 0.03429 0.02784 -0.1132 0.6055 0.0124
-7.000 -0.1865 0.03183 0.02506 -0.1134 0.5968 0.0121
-6.750 -0.1673 0.02944 0.02233 -0.1136 0.5869 0.0118
-6.500 -0.1459 0.02724 0.01976 -0.1136 0.5767 0.0115
-6.250 -0.1227 0.02534 0.01752 -0.1136 0.5675 0.0112
-6.000 -0.0985 0.02365 0.01547 -0.1133 0.5581 0.0110
-5.750 -0.0737 0.02221 0.01373 -0.1130 0.5494 0.0108
-5.500 -0.0483 0.02100 0.01230 -0.1126 0.5420 0.0107
-5.250 -0.0229 0.01999 0.01109 -0.1122 0.5340 0.0106
-5.000 0.0029 0.01909 0.01008 -0.1120 0.5254 0.0106
-4.750 0.0290 0.01831 0.00919 -0.1118 0.5151 0.0106
-4.250 0.0821 0.01705 0.00765 -0.1119 0.4850 0.0108
-4.000 0.1097 0.01655 0.00699 -0.1122 0.4714 0.0110
-3.750 0.1384 0.01609 0.00640 -0.1126 0.4602 0.0113
-3.500 0.1675 0.01570 0.00587 -0.1131 0.4427 0.0117
-3.250 0.1955 0.01547 0.00541 -0.1133 0.4204 0.0122
-3.000 0.2237 0.01530 0.00502 -0.1135 0.4055 0.0129
-2.750 0.2530 0.01507 0.00466 -0.1139 0.3931 0.0143
-2.250 0.3096 0.01487 0.00416 -0.1144 0.3449 0.0436
-2.000 0.3391 0.01466 0.00397 -0.1150 0.3354 0.0976
-1.750 0.3671 0.01466 0.00388 -0.1153 0.2961 0.1168
-1.500 0.3959 0.01458 0.00380 -0.1158 0.2884 0.1645
-1.250 0.4259 0.01434 0.00373 -0.1167 0.2823 0.2615
-1.000 0.4561 0.01411 0.00371 -0.1176 0.2776 0.3307
-0.500 0.5155 0.01383 0.00391 -0.1188 0.2523 0.5010
-0.250 0.5419 0.01410 0.00407 -0.1186 0.2375 0.5137
0.000 0.5690 0.01430 0.00421 -0.1185 0.2320 0.5282
0.250 0.5963 0.01447 0.00432 -0.1184 0.2276 0.5448
0.500 0.6240 0.01461 0.00443 -0.1184 0.2229 0.5581
0.750 0.6514 0.01477 0.00454 -0.1183 0.2155 0.5685
1.000 0.6792 0.01487 0.00465 -0.1183 0.1952 0.5774
1.250 0.7041 0.01528 0.00491 -0.1179 0.1827 0.5852
1.500 0.7301 0.01555 0.00512 -0.1177 0.1764 0.5929
1.750 0.7569 0.01575 0.00530 -0.1175 0.1723 0.6017
2.000 0.7835 0.01597 0.00550 -0.1174 0.1688 0.6148
2.250 0.8098 0.01618 0.00574 -0.1172 0.1664 0.6285
2.500 0.8362 0.01636 0.00595 -0.1169 0.1652 0.6398
2.750 0.8631 0.01652 0.00613 -0.1168 0.1642 0.6487
3.000 0.8896 0.01667 0.00633 -0.1166 0.1631 0.6544
3.250 0.9161 0.01682 0.00655 -0.1164 0.1616 0.6614
3.500 0.9428 0.01698 0.00675 -0.1163 0.1595 0.6684
3.750 0.9698 0.01707 0.00693 -0.1162 0.1478 0.6757
4.000 0.9942 0.01744 0.00726 -0.1158 0.1414 0.6840
4.250 1.0173 0.01784 0.00767 -0.1151 0.1378 0.6913
4.500 1.0412 0.01822 0.00802 -0.1146 0.1338 0.6999
4.750 1.0649 0.01852 0.00838 -0.1140 0.1319 0.7075
5.250 1.1126 0.01910 0.00911 -0.1129 0.1300 0.7275
5.500 1.1362 0.01941 0.00949 -0.1123 0.1293 0.7387
5.750 1.1595 0.01973 0.00990 -0.1117 0.1286 0.7509
6.000 1.1817 0.02004 0.01032 -0.1109 0.1280 0.7622
6.250 1.2036 0.02038 0.01076 -0.1100 0.1273 0.7739
6.500 1.2251 0.02073 0.01121 -0.1092 0.1268 0.7864
6.750 1.2457 0.02111 0.01170 -0.1081 0.1262 0.7995
7.000 1.2652 0.02149 0.01219 -0.1069 0.1256 0.8128
7.250 1.2835 0.02188 0.01270 -0.1055 0.1251 0.8284
7.500 1.3002 0.02229 0.01323 -0.1038 0.1246 0.8483
7.750 1.3136 0.02262 0.01372 -0.1014 0.1235 0.8762
8.000 1.3224 0.02273 0.01401 -0.0980 0.1205 1.0000
8.250 1.3423 0.02321 0.01457 -0.0972 0.1139 1.0000
8.500 1.3636 0.02358 0.01505 -0.0965 0.1038 1.0000
8.750 1.3748 0.02451 0.01595 -0.0946 0.0995 1.0000
9.000 1.3826 0.02565 0.01700 -0.0925 0.0955 1.0000
9.250 1.3885 0.02693 0.01826 -0.0903 0.0926 1.0000
9.500 1.3964 0.02814 0.01952 -0.0885 0.0910 1.0000
9.750 1.4052 0.02937 0.02082 -0.0870 0.0896 1.0000
10.000 1.4127 0.03076 0.02233 -0.0855 0.0874 1.0000
10.250 1.4148 0.03267 0.02434 -0.0840 0.0846 1.0000
10.500 1.4111 0.03525 0.02699 -0.0827 0.0823 1.0000
10.750 1.4404 0.03505 0.02700 -0.0828 0.0739 1.0000
11.000 1.4463 0.03693 0.02893 -0.0820 0.0591 1.0000
11.250 1.4431 0.03981 0.03173 -0.0813 0.0546 1.0000
11.500 1.4438 0.04247 0.03448 -0.0809 0.0507 1.0000
11.750 1.4422 0.04547 0.03758 -0.0806 0.0475 1.0000
12.000 1.4448 0.04810 0.04033 -0.0805 0.0454 1.0000
12.250 1.4524 0.05022 0.04259 -0.0805 0.0430 1.0000
12.500 1.4577 0.05263 0.04512 -0.0806 0.0342 1.0000
12.750 1.4506 0.05656 0.04904 -0.0808 0.0262 1.0000
13.000 1.4478 0.06007 0.05259 -0.0811 0.0220 1.0000
13.250 1.4471 0.06340 0.05599 -0.0815 0.0195 1.0000
13.500 1.4471 0.06674 0.05942 -0.0820 0.0173 1.0000
13.750 1.4464 0.07025 0.06303 -0.0826 0.0154 1.0000
14.000 1.4456 0.07388 0.06676 -0.0833 0.0138 1.0000
14.250 1.4454 0.07750 0.07051 -0.0842 0.0120 1.0000
14.750 1.4365 0.08632 0.07949 -0.0866 0.0051 1.0000
15.000 1.4297 0.09125 0.08451 -0.0881 0.0041 1.0000
15.250 1.4253 0.09593 0.08931 -0.0897 0.0039 1.0000
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Polar data table (+)
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