FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-CL1-152 (fx73cl1152-il) Reynolds number: 200,000 Max Cl/Cd: 53.26 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl1152-il-200000.txt Download as CSV file: xf-fx73cl1152-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0367 0.10547 0.10035 -0.0661 0.6394 0.0660
-9.750 -0.0300 0.10307 0.09784 -0.0672 0.6279 0.0677
-9.500 -0.0584 0.10121 0.09605 -0.0735 0.6248 0.0699
-9.250 -0.0390 0.09774 0.09245 -0.0724 0.6122 0.0703
-9.000 -0.0181 0.09501 0.08966 -0.0713 0.6005 0.0711
-8.750 -0.0048 0.09282 0.08736 -0.0712 0.5917 0.0721
-8.500 0.0054 0.09065 0.08519 -0.0716 0.5838 0.0739
-8.250 0.0087 0.08838 0.08290 -0.0730 0.5778 0.0765
-8.000 -0.0132 0.08513 0.07970 -0.0778 0.5753 0.0785
-7.750 0.0088 0.08275 0.07724 -0.0763 0.5683 0.0792
-7.500 0.0242 0.08067 0.07515 -0.0757 0.5617 0.0803
-7.250 0.0347 0.07863 0.07308 -0.0758 0.5565 0.0818
-7.000 0.0405 0.07650 0.07090 -0.0765 0.5522 0.0840
-6.750 -0.0042 0.07235 0.06688 -0.0859 0.5524 0.0876
-6.500 0.0168 0.07034 0.06488 -0.0817 0.5466 0.0882
-6.250 0.0342 0.06862 0.06315 -0.0800 0.5412 0.0892
-6.000 0.0482 0.06694 0.06142 -0.0795 0.5367 0.0907
-5.750 0.0375 0.05995 0.05436 -0.0955 0.5356 0.0982
-5.500 0.0546 0.05891 0.05330 -0.0917 0.5311 0.0990
-5.250 0.0715 0.05770 0.05213 -0.0896 0.5267 0.1002
-5.000 0.0665 0.03661 0.03009 -0.1111 0.5278 0.0790
-4.750 0.0877 0.03325 0.02649 -0.1122 0.5239 0.0762
-4.500 0.1093 0.02925 0.02195 -0.1138 0.5204 0.0757
-4.250 0.1336 0.02655 0.01876 -0.1144 0.5170 0.0757
-4.000 0.1595 0.02474 0.01647 -0.1146 0.5138 0.0763
-3.750 0.1863 0.02358 0.01489 -0.1145 0.5105 0.0778
-3.500 0.2123 0.02248 0.01372 -0.1144 0.5066 0.0798
-3.250 0.2393 0.02192 0.01312 -0.1141 0.5027 0.0819
-3.000 0.2668 0.02128 0.01230 -0.1139 0.4992 0.0840
-2.750 0.2948 0.02076 0.01152 -0.1136 0.4962 0.0864
-2.500 0.3223 0.02028 0.01092 -0.1135 0.4933 0.0895
-2.250 0.3493 0.01995 0.01065 -0.1132 0.4904 0.0930
-2.000 0.3768 0.01964 0.01025 -0.1128 0.4870 0.0967
-1.750 0.4039 0.01915 0.00978 -0.1125 0.4836 0.1007
-1.500 0.4315 0.01897 0.00957 -0.1122 0.4805 0.1065
-1.250 0.4592 0.01867 0.00924 -0.1120 0.4779 0.1128
-1.000 0.4872 0.01868 0.00917 -0.1118 0.4752 0.1208
-0.750 0.5138 0.01850 0.00911 -0.1114 0.4724 0.1309
-0.500 0.5404 0.01835 0.00907 -0.1110 0.4692 0.1434
-0.250 0.5674 0.01827 0.00908 -0.1107 0.4661 0.1608
0.000 0.5948 0.01823 0.00907 -0.1104 0.4632 0.1859
0.250 0.6222 0.01815 0.00910 -0.1102 0.4605 0.2201
0.500 0.6499 0.01817 0.00917 -0.1100 0.4579 0.2586
0.750 0.6769 0.01836 0.00944 -0.1098 0.4553 0.2962
1.000 0.7025 0.01838 0.00966 -0.1093 0.4527 0.3348
1.250 0.7282 0.01840 0.00988 -0.1088 0.4497 0.3823
1.500 0.7534 0.01830 0.01008 -0.1082 0.4466 0.4556
1.750 0.7757 0.01791 0.01027 -0.1069 0.4439 0.6377
2.000 0.8143 0.01746 0.01028 -0.1084 0.4412 1.0000
2.250 0.8427 0.01781 0.01045 -0.1084 0.4389 1.0000
2.500 0.8695 0.01829 0.01084 -0.1081 0.4365 1.0000
2.750 0.8948 0.01860 0.01117 -0.1076 0.4337 1.0000
3.000 0.9206 0.01892 0.01147 -0.1072 0.4305 1.0000
3.250 0.9470 0.01919 0.01169 -0.1068 0.4275 1.0000
3.500 0.9740 0.01944 0.01186 -0.1065 0.4247 1.0000
3.750 1.0018 0.01971 0.01203 -0.1064 0.4224 1.0000
4.000 1.0299 0.02013 0.01233 -0.1063 0.4202 1.0000
4.250 1.0544 0.02065 0.01287 -0.1058 0.4176 1.0000
4.500 1.0780 0.02108 0.01338 -0.1051 0.4146 1.0000
4.750 1.1025 0.02149 0.01381 -0.1046 0.4116 1.0000
5.000 1.1281 0.02181 0.01412 -0.1042 0.4087 1.0000
5.250 1.1547 0.02206 0.01432 -0.1039 0.4061 1.0000
5.500 1.1826 0.02232 0.01449 -0.1038 0.4039 1.0000
5.750 1.2107 0.02288 0.01493 -0.1039 0.4016 1.0000
6.000 1.2306 0.02343 0.01565 -0.1027 0.3986 1.0000
6.250 1.2523 0.02399 0.01630 -0.1019 0.3954 1.0000
6.500 1.2756 0.02446 0.01681 -0.1013 0.3925 1.0000
6.750 1.3004 0.02482 0.01718 -0.1008 0.3900 1.0000
7.000 1.3266 0.02513 0.01746 -0.1005 0.3878 1.0000
7.250 1.3545 0.02543 0.01768 -0.1005 0.3858 1.0000
7.500 1.3798 0.02606 0.01830 -0.1002 0.3834 1.0000
7.750 1.3945 0.02685 0.01929 -0.0986 0.3800 1.0000
8.000 1.4137 0.02753 0.02007 -0.0975 0.3769 1.0000
8.250 1.4353 0.02806 0.02066 -0.0967 0.3742 1.0000
8.500 1.4595 0.02845 0.02106 -0.0963 0.3720 1.0000
8.750 1.4853 0.02878 0.02137 -0.0960 0.3701 1.0000
9.000 1.5135 0.02912 0.02166 -0.0961 0.3683 1.0000
9.250 1.5317 0.03003 0.02265 -0.0950 0.3658 1.0000
9.500 1.5379 0.03126 0.02412 -0.0925 0.3623 1.0000
9.750 1.5518 0.03218 0.02515 -0.0910 0.3594 1.0000
10.000 1.5699 0.03285 0.02589 -0.0899 0.3570 1.0000
10.250 1.5925 0.03328 0.02634 -0.0893 0.3550 1.0000
10.500 1.6184 0.03356 0.02662 -0.0891 0.3533 1.0000
10.750 1.6488 0.03376 0.02678 -0.0894 0.3517 1.0000
11.000 1.6509 0.03533 0.02853 -0.0867 0.3489 1.0000
11.250 1.6269 0.03794 0.03143 -0.0813 0.3452 1.0000
11.500 1.6113 0.03992 0.03355 -0.0767 0.3424 1.0000
11.750 1.6168 0.04096 0.03465 -0.0745 0.3401 1.0000
12.000 1.6463 0.04086 0.03454 -0.0746 0.3384 1.0000
12.250 1.6840 0.04048 0.03415 -0.0754 0.3369 1.0000
12.500 1.7302 0.04008 0.03369 -0.0774 0.3354 1.0000
12.750 1.0332 0.12777 0.12224 -0.0891 0.2775 1.0000
13.000 1.0606 0.12704 0.12153 -0.0880 0.2764 1.0000
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Polar data table (+)
Polar graphs
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