FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 73-CL1-152 (fx73cl1152-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.36 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl1152-il-1000000.txt Download as CSV file: xf-fx73cl1152-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL1-152
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1324 0.12128 0.11766 -0.0616 0.5733 0.0276
-12.250 -0.6244 0.02987 0.02638 -0.1260 0.7630 0.0286
-12.000 -0.6212 0.02752 0.02373 -0.1268 0.7229 0.0287
-11.500 -0.5956 0.02478 0.02056 -0.1264 0.6677 0.0292
-11.250 -0.5783 0.02372 0.01932 -0.1261 0.6464 0.0294
-11.000 -0.5601 0.02267 0.01808 -0.1257 0.6275 0.0297
-10.750 -0.5403 0.02174 0.01697 -0.1252 0.6102 0.0300
-10.500 -0.5192 0.02090 0.01597 -0.1248 0.5945 0.0303
-10.250 -0.4970 0.02013 0.01504 -0.1244 0.5805 0.0306
-10.000 -0.4738 0.01951 0.01426 -0.1240 0.5670 0.0308
-9.750 -0.4497 0.01903 0.01362 -0.1235 0.5535 0.0311
-9.500 -0.4289 0.01777 0.01219 -0.1231 0.5424 0.0316
-9.250 -0.4050 0.01714 0.01146 -0.1227 0.5309 0.0320
-9.000 -0.3795 0.01670 0.01096 -0.1223 0.5213 0.0324
-8.750 -0.3539 0.01635 0.01052 -0.1219 0.5116 0.0327
-8.500 -0.3278 0.01595 0.01005 -0.1215 0.5037 0.0331
-8.250 -0.3018 0.01560 0.00959 -0.1211 0.4952 0.0336
-8.000 -0.2754 0.01520 0.00911 -0.1207 0.4888 0.0340
-7.750 -0.2488 0.01483 0.00865 -0.1204 0.4823 0.0344
-7.500 -0.2223 0.01455 0.00825 -0.1200 0.4752 0.0348
-7.250 -0.1949 0.01427 0.00790 -0.1196 0.4708 0.0352
-7.000 -0.1692 0.01362 0.00716 -0.1193 0.4657 0.0358
-6.750 -0.1427 0.01325 0.00673 -0.1189 0.4603 0.0364
-6.500 -0.1155 0.01305 0.00649 -0.1185 0.4552 0.0370
-6.250 -0.0876 0.01283 0.00624 -0.1183 0.4521 0.0377
-6.000 -0.0600 0.01260 0.00596 -0.1180 0.4485 0.0383
-5.750 -0.0324 0.01239 0.00569 -0.1176 0.4448 0.0390
-5.500 -0.0048 0.01224 0.00546 -0.1173 0.4409 0.0395
-5.250 0.0224 0.01199 0.00514 -0.1169 0.4371 0.0401
-5.000 0.0498 0.01161 0.00475 -0.1166 0.4351 0.0411
-4.750 0.0779 0.01142 0.00456 -0.1164 0.4327 0.0419
-4.500 0.1059 0.01127 0.00438 -0.1161 0.4298 0.0428
-4.250 0.1340 0.01116 0.00422 -0.1158 0.4269 0.0438
-4.000 0.1620 0.01109 0.00409 -0.1155 0.4239 0.0446
-3.750 0.1891 0.01085 0.00382 -0.1151 0.4206 0.0459
-3.500 0.2171 0.01072 0.00368 -0.1148 0.4185 0.0471
-3.250 0.2455 0.01060 0.00356 -0.1146 0.4170 0.0484
-3.000 0.2739 0.01051 0.00344 -0.1144 0.4151 0.0496
-2.750 0.3020 0.01034 0.00326 -0.1141 0.4130 0.0512
-2.500 0.3302 0.01025 0.00317 -0.1139 0.4107 0.0532
-2.250 0.3583 0.01020 0.00309 -0.1136 0.4084 0.0552
-2.000 0.3862 0.01012 0.00299 -0.1133 0.4058 0.0576
-1.750 0.4138 0.01011 0.00296 -0.1130 0.4025 0.0602
-1.500 0.4420 0.01007 0.00291 -0.1127 0.4007 0.0630
-1.250 0.4704 0.00996 0.00283 -0.1125 0.3993 0.0674
-1.000 0.4987 0.00989 0.00277 -0.1123 0.3977 0.0722
-0.750 0.5270 0.00983 0.00273 -0.1121 0.3958 0.0777
-0.500 0.5551 0.00976 0.00269 -0.1118 0.3939 0.0849
-0.250 0.5832 0.00972 0.00266 -0.1116 0.3918 0.0935
0.000 0.6110 0.00968 0.00265 -0.1113 0.3898 0.1049
0.250 0.6386 0.00967 0.00266 -0.1110 0.3876 0.1213
0.500 0.6657 0.00968 0.00273 -0.1107 0.3848 0.1455
0.750 0.6936 0.00964 0.00278 -0.1104 0.3834 0.1733
1.000 0.7217 0.00959 0.00280 -0.1102 0.3821 0.1968
1.250 0.7498 0.00956 0.00283 -0.1101 0.3806 0.2171
1.500 0.7778 0.00955 0.00287 -0.1098 0.3788 0.2375
1.750 0.8057 0.00954 0.00291 -0.1096 0.3771 0.2592
2.000 0.8334 0.00952 0.00296 -0.1094 0.3753 0.2872
2.250 0.8608 0.00951 0.00303 -0.1091 0.3735 0.3256
2.500 0.8878 0.00949 0.00311 -0.1088 0.3714 0.3763
2.750 0.9140 0.00948 0.00324 -0.1083 0.3689 0.4435
3.000 0.9396 0.00939 0.00340 -0.1078 0.3668 0.5544
3.250 0.9617 0.00898 0.00354 -0.1065 0.3657 0.7672
3.500 1.0057 0.00867 0.00362 -0.1097 0.3639 1.0000
3.750 1.0336 0.00874 0.00368 -0.1095 0.3621 1.0000
4.000 1.0613 0.00883 0.00374 -0.1093 0.3602 1.0000
4.250 1.0889 0.00893 0.00382 -0.1090 0.3582 1.0000
4.500 1.1162 0.00904 0.00390 -0.1087 0.3562 1.0000
4.750 1.1430 0.00919 0.00401 -0.1084 0.3538 1.0000
5.000 1.1691 0.00941 0.00419 -0.1080 0.3507 1.0000
5.250 1.1969 0.00948 0.00427 -0.1078 0.3496 1.0000
5.500 1.2244 0.00956 0.00436 -0.1076 0.3480 1.0000
5.750 1.2517 0.00966 0.00446 -0.1074 0.3461 1.0000
6.000 1.2789 0.00976 0.00455 -0.1071 0.3439 1.0000
6.250 1.3057 0.00987 0.00466 -0.1069 0.3415 1.0000
6.500 1.3321 0.01002 0.00478 -0.1065 0.3389 1.0000
6.750 1.3575 0.01024 0.00496 -0.1060 0.3358 1.0000
7.000 1.3840 0.01037 0.00511 -0.1057 0.3339 1.0000
7.250 1.4109 0.01048 0.00524 -0.1055 0.3321 1.0000
7.500 1.4375 0.01059 0.00537 -0.1052 0.3299 1.0000
7.750 1.4637 0.01072 0.00552 -0.1049 0.3274 1.0000
8.000 1.4894 0.01088 0.00567 -0.1045 0.3248 1.0000
8.250 1.5141 0.01109 0.00586 -0.1039 0.3218 1.0000
8.500 1.5388 0.01132 0.00608 -0.1034 0.3188 1.0000
8.750 1.5649 0.01144 0.00624 -0.1031 0.3168 1.0000
9.000 1.5905 0.01158 0.00641 -0.1027 0.3145 1.0000
9.250 1.6154 0.01176 0.00659 -0.1022 0.3118 1.0000
9.500 1.6396 0.01197 0.00681 -0.1016 0.3091 1.0000
9.750 1.6624 0.01224 0.00707 -0.1008 0.3060 1.0000
10.000 1.6859 0.01248 0.00732 -0.1002 0.3034 1.0000
10.250 1.7105 0.01264 0.00753 -0.0997 0.3012 1.0000
10.500 1.7344 0.01283 0.00776 -0.0991 0.2988 1.0000
10.750 1.7572 0.01307 0.00801 -0.0984 0.2962 1.0000
11.000 1.7787 0.01335 0.00830 -0.0974 0.2932 1.0000
11.250 1.7978 0.01373 0.00866 -0.0961 0.2893 1.0000
11.500 1.8214 0.01389 0.00888 -0.0955 0.2866 1.0000
11.750 1.8429 0.01412 0.00914 -0.0946 0.2823 1.0000
12.000 1.8596 0.01449 0.00949 -0.0929 0.2778 1.0000
12.250 1.8750 0.01487 0.00988 -0.0910 0.2741 1.0000
12.500 1.8949 0.01511 0.01018 -0.0899 0.2711 1.0000
12.750 1.9122 0.01545 0.01055 -0.0884 0.2680 1.0000
13.000 1.9265 0.01593 0.01103 -0.0865 0.2638 1.0000
13.250 1.9401 0.01647 0.01158 -0.0847 0.2591 1.0000
13.500 1.9577 0.01687 0.01204 -0.0836 0.2547 1.0000
13.750 1.9706 0.01753 0.01270 -0.0819 0.2501 1.0000
14.000 1.9813 0.01837 0.01356 -0.0803 0.2454 1.0000
14.250 1.9982 0.01894 0.01420 -0.0794 0.2423 1.0000
14.500 2.0115 0.01978 0.01508 -0.0784 0.2382 1.0000
14.750 2.0204 0.02102 0.01634 -0.0773 0.2338 1.0000
15.000 2.0317 0.02218 0.01755 -0.0765 0.2299 1.0000
15.250 2.0428 0.02342 0.01885 -0.0759 0.2255 1.0000
15.500 2.0458 0.02543 0.02089 -0.0752 0.2201 1.0000
15.750 2.0503 0.02742 0.02294 -0.0748 0.2154 1.0000
16.000 2.0512 0.02981 0.02539 -0.0744 0.2094 1.0000
16.250 2.0423 0.03330 0.02892 -0.0741 0.2035 1.0000
16.500 2.0345 0.03672 0.03240 -0.0738 0.1968 1.0000
16.750 2.0115 0.04178 0.03752 -0.0736 0.1902 1.0000
17.000 1.9911 0.04657 0.04238 -0.0734 0.1840 1.0000
17.250 1.9551 0.05312 0.04899 -0.0733 0.1778 1.0000
17.500 1.9292 0.05871 0.05464 -0.0733 0.1716 1.0000
17.750 1.8904 0.06593 0.06193 -0.0736 0.1658 1.0000
18.000 1.8620 0.07208 0.06814 -0.0740 0.1588 1.0000
18.250 1.8258 0.07924 0.07532 -0.0746 0.1520 1.0000
18.500 1.7987 0.08542 0.08154 -0.0753 0.1452 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 73-CL1-152 (fx73cl1152-il)