74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: 74-130 WP2 (fx74130wp2-il) Reynolds number: 1,000,000 Max Cl/Cd: 150.77 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74130wp2-il-1000000-n5.txt Download as CSV file: xf-fx74130wp2-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: 74-130 WP2
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1809 0.08604 0.08305 -0.0970 0.7293 0.0044
-10.000 -0.1825 0.08112 0.07815 -0.0993 0.7285 0.0048
-6.500 -0.1977 0.02236 0.01788 -0.1055 0.7156 0.0046
-6.250 -0.1831 0.01863 0.01367 -0.1038 0.7148 0.0045
-6.000 -0.1622 0.01644 0.01114 -0.1029 0.7139 0.0045
-5.750 -0.1388 0.01496 0.00939 -0.1025 0.7130 0.0045
-5.500 -0.1141 0.01382 0.00806 -0.1021 0.7122 0.0046
-5.250 -0.0887 0.01299 0.00708 -0.1019 0.7114 0.0046
-5.000 -0.0628 0.01234 0.00632 -0.1018 0.7107 0.0047
-4.750 -0.0382 0.01142 0.00527 -0.1014 0.7099 0.0049
-4.500 -0.0131 0.01074 0.00450 -0.1012 0.7091 0.0054
-4.250 0.0137 0.01041 0.00413 -0.1013 0.7084 0.0057
-4.000 0.0408 0.01012 0.00382 -0.1014 0.7078 0.0061
-3.750 0.0679 0.00984 0.00352 -0.1016 0.7071 0.0065
-3.500 0.0951 0.00956 0.00320 -0.1017 0.7063 0.0067
-3.250 0.1226 0.00932 0.00294 -0.1019 0.7054 0.0070
-3.000 0.1503 0.00912 0.00270 -0.1021 0.7045 0.0074
-2.750 0.1783 0.00898 0.00256 -0.1024 0.7037 0.0078
-2.500 0.2060 0.00874 0.00227 -0.1026 0.7029 0.0086
-2.250 0.2341 0.00858 0.00210 -0.1028 0.7021 0.0096
-2.000 0.2622 0.00844 0.00196 -0.1031 0.7013 0.0140
-1.750 0.2902 0.00826 0.00186 -0.1035 0.7005 0.0348
-1.500 0.3181 0.00805 0.00177 -0.1038 0.6996 0.0759
-1.250 0.3447 0.00749 0.00168 -0.1042 0.6987 0.2347
-1.000 0.3704 0.00652 0.00156 -0.1049 0.6978 0.5188
-0.750 0.3966 0.00590 0.00164 -0.1051 0.6971 0.7502
-0.500 0.4251 0.00598 0.00174 -0.1053 0.6963 0.7808
-0.250 0.4538 0.00607 0.00180 -0.1056 0.6955 0.7935
0.000 0.4825 0.00613 0.00186 -0.1060 0.6946 0.8015
0.250 0.5112 0.00618 0.00190 -0.1063 0.6938 0.8072
0.500 0.5396 0.00622 0.00196 -0.1066 0.6928 0.8121
0.750 0.5684 0.00627 0.00201 -0.1070 0.6919 0.8163
1.000 0.5975 0.00631 0.00204 -0.1075 0.6910 0.8189
1.250 0.6262 0.00632 0.00207 -0.1079 0.6899 0.8205
1.500 0.6550 0.00634 0.00209 -0.1084 0.6886 0.8216
1.750 0.6838 0.00634 0.00211 -0.1088 0.6870 0.8226
2.000 0.7125 0.00634 0.00211 -0.1092 0.6851 0.8234
2.250 0.7412 0.00635 0.00210 -0.1096 0.6828 0.8242
2.500 0.7698 0.00636 0.00214 -0.1100 0.6802 0.8252
2.750 0.7982 0.00635 0.00217 -0.1104 0.6767 0.8261
3.000 0.8266 0.00633 0.00217 -0.1108 0.6728 0.8269
3.250 0.8549 0.00633 0.00217 -0.1111 0.6688 0.8276
3.500 0.8832 0.00633 0.00221 -0.1115 0.6634 0.8284
3.750 0.9111 0.00633 0.00223 -0.1117 0.6563 0.8293
4.000 0.9387 0.00634 0.00226 -0.1119 0.6456 0.8303
4.250 0.9649 0.00640 0.00228 -0.1118 0.6263 0.8312
4.500 0.9894 0.00657 0.00236 -0.1114 0.5977 0.8320
4.750 0.9989 0.00754 0.00286 -0.1083 0.5016 0.8330
5.000 1.0026 0.00880 0.00362 -0.1043 0.3997 0.8343
5.250 1.0125 0.00965 0.00418 -0.1014 0.3365 0.8355
5.500 1.0221 0.01043 0.00472 -0.0985 0.2821 0.8368
5.750 1.0329 0.01108 0.00520 -0.0958 0.2417 0.8382
6.000 1.0383 0.01172 0.00569 -0.0920 0.2045 0.8399
6.250 1.0397 0.01250 0.00631 -0.0876 0.1675 0.8417
6.500 1.0436 0.01330 0.00698 -0.0840 0.1371 0.8434
6.750 1.0499 0.01412 0.00770 -0.0810 0.1126 0.8450
7.000 1.0545 0.01514 0.00858 -0.0780 0.0830 0.8465
7.250 1.0625 0.01608 0.00942 -0.0756 0.0602 0.8480
7.500 1.0706 0.01705 0.01030 -0.0733 0.0393 0.8496
7.750 1.0832 0.01783 0.01105 -0.0717 0.0292 0.8511
8.000 1.0971 0.01857 0.01177 -0.0703 0.0230 0.8527
8.250 1.1122 0.01924 0.01247 -0.0690 0.0194 0.8544
8.500 1.1266 0.01998 0.01321 -0.0677 0.0157 0.8563
8.750 1.1426 0.02063 0.01390 -0.0667 0.0141 0.8581
9.000 1.1561 0.02146 0.01471 -0.0654 0.0103 0.8598
9.500 1.1837 0.02309 0.01637 -0.0629 0.0055 0.8632
9.750 1.1968 0.02396 0.01727 -0.0615 0.0041 0.8653
10.000 1.2104 0.02482 0.01820 -0.0603 0.0036 0.8675
10.250 1.2242 0.02568 0.01911 -0.0592 0.0032 0.8699
10.500 1.2378 0.02658 0.02006 -0.0580 0.0029 0.8724
10.750 1.2511 0.02750 0.02103 -0.0569 0.0027 0.8748
11.000 1.2629 0.02853 0.02212 -0.0557 0.0024 0.8778
11.250 1.2741 0.02962 0.02330 -0.0544 0.0021 0.8813
11.500 1.2851 0.03076 0.02452 -0.0531 0.0021 0.8852
12.000 1.3063 0.03314 0.02708 -0.0506 0.0020 0.8951
12.250 1.3162 0.03442 0.02846 -0.0494 0.0019 0.9024
12.500 1.3269 0.03551 0.02968 -0.0482 0.0019 0.9152
12.750 1.3382 0.03678 0.03114 -0.0474 0.0019 0.9667
13.250 1.3575 0.03964 0.03415 -0.0454 0.0018 1.0000
13.500 1.3661 0.04125 0.03585 -0.0445 0.0018 1.0000
13.750 1.3747 0.04290 0.03758 -0.0437 0.0017 1.0000
14.000 1.3815 0.04477 0.03955 -0.0428 0.0017 1.0000
14.250 1.3892 0.04659 0.04146 -0.0421 0.0016 1.0000
14.500 1.3963 0.04849 0.04345 -0.0414 0.0016 1.0000
14.750 1.4011 0.05069 0.04576 -0.0406 0.0016 1.0000
15.000 1.4051 0.05303 0.04821 -0.0400 0.0016 1.0000
15.250 1.4099 0.05535 0.05063 -0.0395 0.0015 1.0000
15.500 1.4127 0.05794 0.05336 -0.0390 0.0015 1.0000
15.750 1.4157 0.06057 0.05610 -0.0387 0.0014 1.0000
16.000 1.4176 0.06340 0.05905 -0.0385 0.0014 1.0000
16.250 1.4195 0.06632 0.06207 -0.0384 0.0013 1.0000
16.500 1.4175 0.06984 0.06573 -0.0384 0.0013 1.0000
16.750 1.4179 0.07311 0.06912 -0.0387 0.0013 1.0000
17.000 1.4167 0.07671 0.07283 -0.0392 0.0013 1.0000
17.250 1.4131 0.08076 0.07701 -0.0398 0.0012 1.0000
17.500 1.4076 0.08524 0.08164 -0.0408 0.0012 1.0000
17.750 1.4006 0.09010 0.08665 -0.0420 0.0012 1.0000
18.000 1.3943 0.09499 0.09167 -0.0435 0.0012 1.0000
18.250 1.3863 0.10032 0.09713 -0.0454 0.0012 1.0000
18.500 1.3759 0.10625 0.10322 -0.0478 0.0012 1.0000
18.750 1.3640 0.11266 0.10978 -0.0506 0.0012 1.0000
19.000 1.3529 0.11911 0.11637 -0.0537 0.0012 1.0000
19.250 1.3395 0.12617 0.12358 -0.0573 0.0011 1.0000
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Polar data table (+)
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