FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 200,000 Max Cl/Cd: 71.87 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61147-il-200000-n5.txt Download as CSV file: xf-fx61147-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-147 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4443 0.07016 0.06676 -0.0588 1.0000 0.0089
-9.750 -0.4692 0.06435 0.06090 -0.0611 1.0000 0.0088
-9.500 -0.4858 0.06152 0.05807 -0.0609 1.0000 0.0087
-9.250 -0.4988 0.05558 0.05195 -0.0664 0.9954 0.0087
-9.000 -0.5103 0.04925 0.04531 -0.0723 0.9844 0.0086
-8.750 -0.5090 0.04283 0.03844 -0.0776 0.9729 0.0087
-8.500 -0.5032 0.03643 0.03136 -0.0806 0.9631 0.0088
-8.250 -0.4893 0.03257 0.02704 -0.0815 0.9537 0.0090
-8.000 -0.4617 0.03019 0.02438 -0.0839 0.9491 0.0094
-7.750 -0.4398 0.02838 0.02235 -0.0843 0.9403 0.0097
-7.500 -0.4092 0.02647 0.02017 -0.0861 0.9358 0.0105
-7.250 -0.3845 0.02479 0.01819 -0.0862 0.9272 0.0115
-7.000 -0.3525 0.02322 0.01640 -0.0878 0.9220 0.0130
-6.750 -0.3239 0.02217 0.01522 -0.0885 0.9135 0.0142
-6.500 -0.2896 0.02071 0.01357 -0.0901 0.9078 0.0156
-6.250 -0.2588 0.01951 0.01224 -0.0910 0.8991 0.0174
-6.000 -0.2200 0.01867 0.01137 -0.0938 0.8925 0.0200
-5.750 -0.1865 0.01779 0.01037 -0.0952 0.8820 0.0222
-5.500 -0.1487 0.01679 0.00933 -0.0979 0.8722 0.0254
-5.250 -0.1082 0.01593 0.00837 -0.1010 0.8619 0.0282
-5.000 -0.0703 0.01515 0.00749 -0.1037 0.8485 0.0322
-4.750 -0.0328 0.01453 0.00675 -0.1061 0.8334 0.0376
-4.500 0.0031 0.01393 0.00606 -0.1083 0.8171 0.0467
-4.250 0.0369 0.01338 0.00548 -0.1100 0.7999 0.0699
-4.000 0.0700 0.01235 0.00487 -0.1124 0.7821 0.1831
-3.750 0.1047 0.01088 0.00439 -0.1158 0.7643 0.4479
-3.500 0.1332 0.01082 0.00460 -0.1158 0.7468 0.5529
-3.250 0.1607 0.01108 0.00482 -0.1152 0.7300 0.5985
-3.000 0.1869 0.01151 0.00514 -0.1143 0.7134 0.6294
-2.750 0.2130 0.01186 0.00535 -0.1134 0.6978 0.6452
-2.500 0.2402 0.01204 0.00536 -0.1131 0.6833 0.6530
-2.250 0.2678 0.01215 0.00531 -0.1130 0.6698 0.6590
-2.000 0.2943 0.01229 0.00532 -0.1126 0.6570 0.6635
-1.750 0.3226 0.01237 0.00525 -0.1128 0.6448 0.6695
-1.500 0.3499 0.01248 0.00523 -0.1126 0.6336 0.6737
-1.250 0.3763 0.01261 0.00525 -0.1123 0.6234 0.6773
-1.000 0.4039 0.01271 0.00524 -0.1123 0.6132 0.6819
-0.750 0.4329 0.01278 0.00518 -0.1127 0.6034 0.6871
-0.250 0.4857 0.01301 0.00527 -0.1120 0.5851 0.6931
0.000 0.5134 0.01311 0.00528 -0.1121 0.5767 0.6971
0.250 0.5426 0.01319 0.00526 -0.1126 0.5677 0.7017
0.500 0.5687 0.01330 0.00533 -0.1123 0.5596 0.7041
0.750 0.5952 0.01342 0.00541 -0.1120 0.5519 0.7068
1.000 0.6224 0.01352 0.00548 -0.1120 0.5444 0.7102
1.250 0.6507 0.01363 0.00552 -0.1123 0.5371 0.7142
1.500 0.6786 0.01374 0.00559 -0.1125 0.5301 0.7174
1.750 0.7048 0.01386 0.00571 -0.1122 0.5233 0.7198
2.000 0.7316 0.01399 0.00582 -0.1121 0.5172 0.7224
2.250 0.7589 0.01410 0.00593 -0.1121 0.5103 0.7255
2.500 0.7869 0.01425 0.00603 -0.1124 0.5041 0.7290
2.750 0.8146 0.01436 0.00615 -0.1126 0.4971 0.7320
3.000 0.8404 0.01451 0.00629 -0.1123 0.4908 0.7341
3.250 0.8668 0.01463 0.00647 -0.1121 0.4840 0.7365
3.500 0.8933 0.01479 0.00663 -0.1120 0.4777 0.7394
3.750 0.9206 0.01494 0.00679 -0.1121 0.4715 0.7424
4.000 0.9485 0.01510 0.00698 -0.1124 0.4649 0.7456
4.250 0.9740 0.01527 0.00717 -0.1121 0.4595 0.7477
4.500 0.9998 0.01542 0.00740 -0.1118 0.4530 0.7500
4.750 1.0256 0.01560 0.00761 -0.1116 0.4470 0.7525
5.000 1.0520 0.01578 0.00786 -0.1115 0.4409 0.7552
5.250 1.0786 0.01597 0.00811 -0.1115 0.4348 0.7583
5.500 1.1050 0.01620 0.00835 -0.1115 0.4295 0.7610
5.750 1.1298 0.01637 0.00866 -0.1111 0.4228 0.7630
6.000 1.1544 0.01659 0.00893 -0.1107 0.4169 0.7654
6.250 1.1796 0.01681 0.00925 -0.1104 0.4107 0.7680
6.500 1.2044 0.01704 0.00956 -0.1100 0.4040 0.7708
6.750 1.2289 0.01728 0.00988 -0.1097 0.3955 0.7736
7.000 1.2515 0.01753 0.01017 -0.1089 0.3865 0.7761
7.250 1.2733 0.01775 0.01051 -0.1080 0.3758 0.7784
7.500 1.2944 0.01801 0.01084 -0.1070 0.3643 0.7809
7.750 1.3154 0.01831 0.01121 -0.1060 0.3535 0.7835
8.000 1.3355 0.01865 0.01161 -0.1049 0.3416 0.7864
8.500 1.3698 0.01944 0.01248 -0.1016 0.3061 0.7918
8.750 1.3812 0.01996 0.01298 -0.0991 0.2856 0.7944
9.000 1.3922 0.02058 0.01358 -0.0965 0.2622 0.7972
9.250 1.4005 0.02141 0.01433 -0.0937 0.2358 0.8004
9.500 1.4056 0.02249 0.01531 -0.0907 0.2050 0.8039
9.750 1.4054 0.02383 0.01650 -0.0870 0.1708 0.8066
10.000 1.4031 0.02542 0.01795 -0.0834 0.1400 0.8097
10.250 1.4011 0.02713 0.01956 -0.0803 0.1153 0.8128
10.500 1.4002 0.02892 0.02129 -0.0775 0.0952 0.8161
10.750 1.3995 0.03078 0.02315 -0.0751 0.0801 0.8194
11.250 1.3957 0.03497 0.02738 -0.0709 0.0566 0.8264
11.500 1.3939 0.03734 0.02979 -0.0694 0.0468 0.8303
11.750 1.3913 0.03993 0.03242 -0.0682 0.0385 0.8338
12.000 1.3879 0.04270 0.03525 -0.0672 0.0323 0.8373
12.250 1.3843 0.04568 0.03830 -0.0665 0.0273 0.8412
12.500 1.3824 0.04868 0.04139 -0.0662 0.0234 0.8457
12.750 1.3786 0.05195 0.04479 -0.0659 0.0201 0.8502
13.000 1.3759 0.05520 0.04818 -0.0659 0.0175 0.8555
13.250 1.3717 0.05878 0.05188 -0.0660 0.0148 0.8612
13.500 1.3668 0.06245 0.05568 -0.0662 0.0127 0.8677
14.000 1.3544 0.07025 0.06375 -0.0669 0.0097 0.8868
14.250 1.3446 0.07362 0.06732 -0.0661 0.0089 0.9376
14.500 1.3400 0.07787 0.07171 -0.0673 0.0081 1.0000
14.750 1.3356 0.08238 0.07634 -0.0687 0.0075 1.0000
15.000 1.3303 0.08711 0.08118 -0.0703 0.0070 1.0000
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