74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.16 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74130wp2mod-il-1000000.txt Download as CSV file: xf-fx74130wp2mod-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: 74-130 WP2 MOD
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1707 0.08181 0.07921 -0.1023 0.8016 0.0082
-9.750 -0.1669 0.07899 0.07640 -0.1036 0.8003 0.0084
-9.500 -0.1659 0.07456 0.07199 -0.1060 0.7986 0.0081
-9.250 -0.1653 0.07165 0.06909 -0.1074 0.7970 0.0084
-9.000 -0.1638 0.06857 0.06602 -0.1091 0.7951 0.0086
-8.750 -0.1676 0.06438 0.06184 -0.1121 0.7928 0.0087
-8.500 -0.1814 0.05926 0.05673 -0.1160 0.7905 0.0087
-8.250 -0.1950 0.05625 0.05371 -0.1157 0.7882 0.0088
-8.000 -0.2028 0.05237 0.04976 -0.1159 0.7858 0.0088
-7.750 -0.2013 0.04960 0.04692 -0.1157 0.7838 0.0090
-7.500 -0.1989 0.04635 0.04356 -0.1154 0.7823 0.0091
-7.250 -0.1934 0.04326 0.04035 -0.1149 0.7808 0.0095
-7.000 -0.1855 0.04014 0.03708 -0.1141 0.7792 0.0098
-6.750 -0.1754 0.03699 0.03375 -0.1132 0.7777 0.0103
-6.500 -0.1587 0.03408 0.03066 -0.1120 0.7765 0.0114
-6.250 -0.1361 0.03263 0.02904 -0.1111 0.7752 0.0120
-6.000 -0.1206 0.03022 0.02641 -0.1100 0.7738 0.0121
-5.750 -0.1044 0.02778 0.02373 -0.1089 0.7723 0.0121
-5.500 -0.0860 0.02565 0.02136 -0.1080 0.7708 0.0121
-4.250 0.0223 0.01296 0.00733 -0.1039 0.7633 0.0097
-4.000 0.0469 0.01141 0.00562 -0.1030 0.7619 0.0090
-3.750 0.0726 0.01076 0.00492 -0.1028 0.7603 0.0094
-3.500 0.0990 0.01030 0.00443 -0.1027 0.7585 0.0102
-3.250 0.1257 0.00989 0.00398 -0.1026 0.7567 0.0109
-3.000 0.1528 0.00955 0.00359 -0.1027 0.7550 0.0115
-2.750 0.1801 0.00925 0.00323 -0.1028 0.7532 0.0118
-2.500 0.2075 0.00896 0.00287 -0.1029 0.7514 0.0127
-2.250 0.2349 0.00867 0.00253 -0.1029 0.7494 0.0145
-2.000 0.2623 0.00835 0.00226 -0.1030 0.7473 0.0322
-1.750 0.2876 0.00757 0.00208 -0.1032 0.7450 0.2193
-1.250 0.3374 0.00584 0.00200 -0.1035 0.7406 0.7674
-1.000 0.3655 0.00596 0.00209 -0.1035 0.7385 0.7950
-0.750 0.3934 0.00609 0.00220 -0.1035 0.7361 0.8090
-0.500 0.4208 0.00618 0.00231 -0.1033 0.7335 0.8211
-0.250 0.4478 0.00624 0.00239 -0.1031 0.7305 0.8297
0.000 0.4757 0.00625 0.00238 -0.1031 0.7275 0.8357
0.250 0.5033 0.00627 0.00238 -0.1031 0.7247 0.8403
0.500 0.5315 0.00631 0.00240 -0.1033 0.7215 0.8449
0.750 0.5595 0.00628 0.00239 -0.1035 0.7176 0.8484
1.000 0.5873 0.00625 0.00235 -0.1036 0.7138 0.8508
1.250 0.6155 0.00624 0.00232 -0.1039 0.7103 0.8527
1.500 0.6438 0.00623 0.00232 -0.1042 0.7057 0.8544
1.750 0.6723 0.00621 0.00231 -0.1046 0.7006 0.8559
2.000 0.7007 0.00621 0.00228 -0.1049 0.6960 0.8573
2.250 0.7292 0.00621 0.00230 -0.1053 0.6896 0.8585
2.500 0.7575 0.00622 0.00228 -0.1057 0.6834 0.8594
2.750 0.7859 0.00624 0.00232 -0.1061 0.6759 0.8603
3.000 0.8136 0.00627 0.00232 -0.1063 0.6682 0.8612
3.250 0.8410 0.00629 0.00234 -0.1065 0.6588 0.8620
3.500 0.8678 0.00635 0.00237 -0.1065 0.6473 0.8630
3.750 0.8937 0.00645 0.00245 -0.1064 0.6333 0.8640
4.000 0.9192 0.00658 0.00254 -0.1062 0.6188 0.8650
4.250 0.9444 0.00674 0.00265 -0.1059 0.6035 0.8658
4.500 0.9700 0.00689 0.00277 -0.1058 0.5903 0.8667
4.750 0.9952 0.00705 0.00292 -0.1056 0.5763 0.8677
5.000 1.0193 0.00727 0.00308 -0.1051 0.5591 0.8688
5.250 1.0444 0.00743 0.00324 -0.1049 0.5456 0.8700
5.500 1.0697 0.00759 0.00340 -0.1048 0.5327 0.8710
5.750 1.0936 0.00781 0.00359 -0.1043 0.5141 0.8720
6.000 1.1149 0.00814 0.00384 -0.1034 0.4826 0.8731
6.250 1.1203 0.00919 0.00443 -0.0997 0.3879 0.8745
6.500 1.1166 0.01055 0.00527 -0.0945 0.2901 0.8766
6.750 1.1182 0.01145 0.00590 -0.0901 0.2305 0.8787
7.000 1.1114 0.01254 0.00666 -0.0843 0.1695 0.8816
7.250 1.1095 0.01358 0.00747 -0.0797 0.1217 0.8844
7.500 1.1127 0.01456 0.00828 -0.0762 0.0882 0.8868
7.750 1.1183 0.01553 0.00912 -0.0733 0.0609 0.8891
8.000 1.1267 0.01640 0.00994 -0.0709 0.0441 0.8917
8.250 1.1379 0.01718 0.01070 -0.0690 0.0337 0.8944
8.500 1.1507 0.01791 0.01143 -0.0673 0.0272 0.8972
8.750 1.1639 0.01866 0.01220 -0.0658 0.0219 0.9001
9.000 1.1767 0.01946 0.01299 -0.0643 0.0180 0.9033
9.250 1.1886 0.02026 0.01383 -0.0626 0.0132 0.9077
9.500 1.1962 0.02137 0.01494 -0.0604 0.0077 0.9134
9.750 1.2026 0.02258 0.01623 -0.0580 0.0060 0.9209
10.000 1.2133 0.02345 0.01720 -0.0562 0.0055 0.9328
10.250 1.2267 0.02441 0.01833 -0.0552 0.0051 0.9735
10.500 1.2396 0.02537 0.01934 -0.0542 0.0047 1.0000
10.750 1.2509 0.02652 0.02054 -0.0529 0.0045 1.0000
11.000 1.2608 0.02778 0.02186 -0.0516 0.0042 1.0000
11.250 1.2685 0.02924 0.02340 -0.0501 0.0040 1.0000
11.500 1.2711 0.03113 0.02540 -0.0481 0.0038 1.0000
11.750 1.2720 0.03324 0.02764 -0.0461 0.0037 1.0000
12.000 1.2756 0.03519 0.02970 -0.0445 0.0037 1.0000
12.250 1.2820 0.03697 0.03156 -0.0431 0.0036 1.0000
12.500 1.2906 0.03858 0.03326 -0.0421 0.0036 1.0000
12.750 1.2989 0.04026 0.03503 -0.0412 0.0035 1.0000
13.000 1.3069 0.04201 0.03688 -0.0402 0.0035 1.0000
13.250 1.3123 0.04408 0.03907 -0.0392 0.0034 1.0000
13.500 1.3201 0.04596 0.04105 -0.0384 0.0034 1.0000
13.750 1.3251 0.04819 0.04340 -0.0375 0.0033 1.0000
14.000 1.3310 0.05034 0.04566 -0.0369 0.0032 1.0000
14.250 1.3355 0.05274 0.04819 -0.0362 0.0031 1.0000
14.500 1.3383 0.05541 0.05099 -0.0356 0.0030 1.0000
14.750 1.3405 0.05821 0.05393 -0.0352 0.0030 1.0000
15.000 1.3412 0.06125 0.05711 -0.0349 0.0028 1.0000
15.250 1.3401 0.06464 0.06065 -0.0347 0.0028 1.0000
15.500 1.3379 0.06826 0.06442 -0.0347 0.0027 1.0000
15.750 1.3328 0.07238 0.06872 -0.0349 0.0027 1.0000
16.000 1.3259 0.07690 0.07342 -0.0354 0.0027 1.0000
16.250 1.3175 0.08181 0.07850 -0.0363 0.0027 1.0000
16.500 1.3067 0.08727 0.08415 -0.0375 0.0026 1.0000
16.750 1.2914 0.09368 0.09077 -0.0392 0.0027 1.0000
17.000 1.2768 0.10021 0.09749 -0.0415 0.0026 1.0000
17.250 1.2574 0.10796 0.10545 -0.0446 0.0027 1.0000
17.500 1.2366 0.11638 0.11407 -0.0484 0.0027 1.0000
17.750 1.2147 0.12550 0.12340 -0.0531 0.0027 1.0000
18.000 1.1922 0.13542 0.13350 -0.0588 0.0028 1.0000
18.250 1.1697 0.14602 0.14429 -0.0652 0.0028 1.0000
18.500 1.1481 0.15715 0.15558 -0.0723 0.0029 1.0000
18.750 1.1230 0.17024 0.16882 -0.0805 0.0029 1.0000
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Polar data table (+)
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