74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: 74-130 WP2 (fx74130wp2-il) Reynolds number: 1,000,000 Max Cl/Cd: 161.37 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74130wp2-il-1000000.txt Download as CSV file: xf-fx74130wp2-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1567 0.08528 0.08240 -0.1009 0.7529 0.0077
-9.750 -0.1679 0.07965 0.07681 -0.1029 0.7520 0.0082
-9.500 -0.1647 0.07660 0.07376 -0.1044 0.7509 0.0084
-9.250 -0.1656 0.07249 0.06966 -0.1067 0.7497 0.0083
-9.000 -0.1622 0.06988 0.06708 -0.1081 0.7490 0.0086
-8.750 -0.1634 0.06627 0.06351 -0.1104 0.7481 0.0088
-8.500 -0.1784 0.06049 0.05776 -0.1152 0.7470 0.0086
-8.250 -0.1936 0.05703 0.05429 -0.1154 0.7458 0.0087
-8.000 -0.1992 0.05379 0.05101 -0.1156 0.7447 0.0088
-7.750 -0.2010 0.05031 0.04745 -0.1156 0.7437 0.0089
-7.500 -0.1979 0.04727 0.04432 -0.1154 0.7426 0.0092
-7.250 -0.1928 0.04406 0.04100 -0.1149 0.7417 0.0094
-7.000 -0.1851 0.04085 0.03764 -0.1143 0.7406 0.0097
-6.750 -0.1750 0.03761 0.03423 -0.1134 0.7396 0.0102
-6.500 -0.1579 0.03470 0.03111 -0.1123 0.7387 0.0113
-6.250 -0.1356 0.03320 0.02942 -0.1115 0.7378 0.0119
-6.000 -0.1204 0.03075 0.02674 -0.1104 0.7368 0.0119
-5.750 -0.1037 0.02849 0.02425 -0.1094 0.7359 0.0120
-5.500 -0.0858 0.02617 0.02169 -0.1084 0.7353 0.0120
-4.250 0.0226 0.01337 0.00760 -0.1045 0.7311 0.0096
-4.000 0.0476 0.01195 0.00603 -0.1038 0.7302 0.0092
-3.750 0.0737 0.01136 0.00539 -0.1036 0.7294 0.0097
-3.500 0.1001 0.01089 0.00488 -0.1036 0.7285 0.0103
-3.250 0.1269 0.01052 0.00447 -0.1036 0.7277 0.0110
-3.000 0.1539 0.01018 0.00408 -0.1037 0.7270 0.0114
-2.750 0.1814 0.00992 0.00378 -0.1038 0.7261 0.0118
-2.500 0.2086 0.00956 0.00335 -0.1039 0.7253 0.0128
-2.250 0.2364 0.00933 0.00305 -0.1041 0.7244 0.0141
-2.000 0.2642 0.00908 0.00282 -0.1043 0.7236 0.0314
-1.750 0.2899 0.00846 0.00275 -0.1046 0.7226 0.2052
-1.500 0.3150 0.00758 0.00265 -0.1051 0.7219 0.4600
-1.250 0.3396 0.00676 0.00277 -0.1050 0.7212 0.7638
-1.000 0.3675 0.00690 0.00293 -0.1051 0.7203 0.7945
-0.750 0.3953 0.00702 0.00306 -0.1051 0.7194 0.8088
-0.500 0.4227 0.00716 0.00320 -0.1050 0.7184 0.8213
-0.250 0.4500 0.00728 0.00334 -0.1048 0.7174 0.8299
0.000 0.4778 0.00735 0.00341 -0.1049 0.7165 0.8359
0.250 0.5053 0.00742 0.00349 -0.1050 0.7155 0.8408
0.500 0.5339 0.00749 0.00355 -0.1053 0.7145 0.8453
0.750 0.5623 0.00752 0.00357 -0.1056 0.7136 0.8487
1.000 0.5905 0.00754 0.00360 -0.1058 0.7127 0.8510
1.250 0.6192 0.00757 0.00361 -0.1062 0.7117 0.8529
1.500 0.6483 0.00758 0.00361 -0.1067 0.7104 0.8545
1.750 0.6773 0.00767 0.00369 -0.1072 0.7086 0.8560
2.000 0.7058 0.00763 0.00368 -0.1077 0.7071 0.8574
2.250 0.7344 0.00761 0.00368 -0.1081 0.7052 0.8586
2.500 0.7632 0.00757 0.00365 -0.1086 0.7030 0.8596
2.750 0.7925 0.00750 0.00359 -0.1091 0.7005 0.8605
3.000 0.8221 0.00741 0.00350 -0.1097 0.6981 0.8612
3.250 0.8513 0.00737 0.00344 -0.1102 0.6955 0.8620
3.500 0.8789 0.00728 0.00341 -0.1104 0.6922 0.8629
3.750 0.9070 0.00715 0.00334 -0.1107 0.6880 0.8639
4.000 0.9357 0.00701 0.00320 -0.1110 0.6835 0.8648
4.250 0.9632 0.00691 0.00314 -0.1112 0.6772 0.8656
4.500 0.9911 0.00682 0.00309 -0.1114 0.6714 0.8664
4.750 1.0184 0.00673 0.00304 -0.1115 0.6609 0.8673
5.000 1.0456 0.00669 0.00303 -0.1116 0.6497 0.8682
5.250 1.0723 0.00670 0.00306 -0.1116 0.6362 0.8693
5.500 1.0973 0.00680 0.00311 -0.1113 0.6130 0.8705
5.750 1.1118 0.00738 0.00341 -0.1090 0.5427 0.8719
6.000 1.1168 0.00851 0.00410 -0.1051 0.4556 0.8734
6.250 1.1196 0.00964 0.00484 -0.1010 0.3757 0.8749
6.500 1.1169 0.01077 0.00559 -0.0959 0.2993 0.8771
6.750 1.1085 0.01175 0.00630 -0.0897 0.2418 0.8797
7.000 1.0995 0.01290 0.00719 -0.0837 0.1902 0.8829
7.250 1.0954 0.01411 0.00821 -0.0792 0.1477 0.8858
7.500 1.0927 0.01550 0.00936 -0.0753 0.1043 0.8883
7.750 1.0978 0.01659 0.01032 -0.0726 0.0753 0.8909
8.000 1.1055 0.01760 0.01124 -0.0703 0.0541 0.8935
8.250 1.1164 0.01848 0.01209 -0.0685 0.0407 0.8961
8.500 1.1285 0.01932 0.01290 -0.0669 0.0312 0.8987
8.750 1.1410 0.02018 0.01374 -0.0654 0.0243 0.9015
9.000 1.1554 0.02090 0.01449 -0.0642 0.0205 0.9046
9.250 1.1670 0.02177 0.01537 -0.0626 0.0153 0.9088
9.500 1.1778 0.02275 0.01635 -0.0609 0.0097 0.9134
9.750 1.1864 0.02387 0.01750 -0.0589 0.0064 0.9194
10.000 1.1975 0.02478 0.01851 -0.0573 0.0059 0.9284
10.250 1.2101 0.02561 0.01949 -0.0559 0.0053 0.9560
10.500 1.2259 0.02659 0.02054 -0.0554 0.0048 1.0000
10.750 1.2388 0.02765 0.02164 -0.0544 0.0046 1.0000
11.000 1.2491 0.02892 0.02298 -0.0531 0.0042 1.0000
11.250 1.2564 0.03044 0.02458 -0.0515 0.0040 1.0000
11.500 1.2641 0.03196 0.02619 -0.0500 0.0039 1.0000
11.750 1.2674 0.03389 0.02825 -0.0482 0.0038 1.0000
12.000 1.2721 0.03577 0.03023 -0.0466 0.0037 1.0000
12.250 1.2813 0.03730 0.03185 -0.0455 0.0037 1.0000
12.500 1.2924 0.03866 0.03329 -0.0446 0.0036 1.0000
12.750 1.3010 0.04031 0.03504 -0.0436 0.0035 1.0000
13.000 1.3096 0.04199 0.03682 -0.0426 0.0035 1.0000
13.250 1.3174 0.04378 0.03870 -0.0417 0.0034 1.0000
13.500 1.3240 0.04575 0.04079 -0.0407 0.0033 1.0000
13.750 1.3312 0.04770 0.04284 -0.0398 0.0032 1.0000
14.000 1.3358 0.04997 0.04524 -0.0389 0.0031 1.0000
14.250 1.3414 0.05219 0.04757 -0.0382 0.0030 1.0000
14.500 1.3453 0.05466 0.05016 -0.0375 0.0029 1.0000
14.750 1.3471 0.05743 0.05308 -0.0368 0.0028 1.0000
15.000 1.3471 0.06053 0.05634 -0.0362 0.0028 1.0000
15.250 1.3468 0.06370 0.05966 -0.0358 0.0027 1.0000
15.500 1.3434 0.06742 0.06355 -0.0355 0.0027 1.0000
15.750 1.3389 0.07136 0.06765 -0.0355 0.0027 1.0000
16.000 1.3324 0.07572 0.07219 -0.0357 0.0026 1.0000
16.250 1.3233 0.08065 0.07730 -0.0363 0.0026 1.0000
16.500 1.3100 0.08646 0.08332 -0.0374 0.0026 1.0000
16.750 1.2964 0.09251 0.08957 -0.0389 0.0026 1.0000
17.000 1.2801 0.09934 0.09662 -0.0411 0.0026 1.0000
17.250 1.2597 0.10732 0.10480 -0.0442 0.0027 1.0000
17.500 1.2367 0.11623 0.11394 -0.0482 0.0027 1.0000
17.750 1.2126 0.12594 0.12386 -0.0533 0.0028 1.0000
18.000 1.1886 0.13628 0.13441 -0.0592 0.0028 1.0000
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Polar data table (+)
Polar graphs
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