74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: 74-130 WP2 (fx74130wp2-il) Reynolds number: 200,000 Max Cl/Cd: 72.55 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74130wp2-il-200000.txt Download as CSV file: xf-fx74130wp2-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1439 0.09623 0.09217 -0.1044 0.8622 0.0367
-10.000 -0.1435 0.09330 0.08925 -0.1071 0.8605 0.0377
-9.750 -0.1457 0.09028 0.08629 -0.1105 0.8584 0.0383
-9.500 -0.1056 0.07508 0.07143 -0.1073 0.8514 0.0395
-9.250 -0.0920 0.07184 0.06817 -0.1054 0.8504 0.0410
-9.000 -0.0861 0.06881 0.06514 -0.1056 0.8492 0.0422
-8.750 -0.0846 0.06549 0.06182 -0.1066 0.8479 0.0432
-8.500 -0.0854 0.06206 0.05840 -0.1079 0.8465 0.0444
-8.250 -0.1701 0.06768 0.06380 -0.1226 0.8472 0.0402
-8.000 -0.1638 0.06525 0.06137 -0.1220 0.8457 0.0411
-7.750 -0.1618 0.06286 0.05898 -0.1220 0.8437 0.0422
-7.500 -0.1615 0.06028 0.05637 -0.1222 0.8418 0.0431
-7.250 -0.1599 0.05772 0.05374 -0.1223 0.8400 0.0445
-7.000 -0.1569 0.05512 0.05103 -0.1223 0.8383 0.0462
-6.750 -0.1521 0.05255 0.04827 -0.1221 0.8366 0.0488
-6.250 -0.1419 0.04675 0.04190 -0.1204 0.8331 0.0537
-6.000 -0.1285 0.04468 0.03984 -0.1199 0.8318 0.0558
-5.750 -0.1164 0.04306 0.03812 -0.1192 0.8300 0.0590
-5.500 -0.1084 0.04167 0.03621 -0.1173 0.8279 0.0667
-5.250 -0.0939 0.03942 0.03404 -0.1168 0.8259 0.0693
-4.750 -0.0632 0.03638 0.03063 -0.1148 0.8224 0.0838
-4.500 -0.0460 0.03502 0.02905 -0.1140 0.8211 0.0968
-4.250 -0.0105 0.03102 0.02385 -0.1104 0.8201 0.0394
-4.000 0.0137 0.02805 0.02069 -0.1098 0.8191 0.0347
-3.750 0.0217 0.02801 0.02052 -0.1071 0.8159 0.0360
-3.500 0.0303 0.02790 0.02028 -0.1044 0.8134 0.0364
-3.250 0.0449 0.02736 0.01959 -0.1024 0.8112 0.0363
-3.000 0.0669 0.02649 0.01861 -0.1013 0.8093 0.0357
-2.750 0.0894 0.02583 0.01788 -0.1003 0.8079 0.0358
-2.500 0.1133 0.02531 0.01730 -0.0997 0.8068 0.0370
-2.250 0.1405 0.02482 0.01677 -0.0996 0.8058 0.0391
-2.000 0.1696 0.02410 0.01601 -0.0999 0.8049 0.0527
-1.750 0.1169 0.02647 0.01842 -0.0883 0.7969 0.0437
-1.500 0.1395 0.02524 0.01801 -0.0883 0.7952 0.2388
-1.250 0.1366 0.02433 0.01916 -0.0809 0.7933 0.8316
-1.000 0.1409 0.02476 0.01963 -0.0735 0.7917 0.8847
-0.500 0.3128 0.02528 0.01978 -0.0909 0.7925 0.9784
-0.250 0.3598 0.02524 0.01960 -0.0948 0.7917 0.9824
0.000 0.3499 0.02690 0.02129 -0.0915 0.7840 0.9929
0.250 0.3870 0.02708 0.02139 -0.0940 0.7818 0.9957
0.500 0.4291 0.02712 0.02134 -0.0972 0.7803 0.9973
0.750 0.4711 0.02711 0.02126 -0.1002 0.7791 0.9987
1.000 0.5120 0.02705 0.02114 -0.1029 0.7781 0.9998
1.250 0.4293 0.02878 0.02293 -0.0851 0.7661 1.0000
1.500 0.3915 0.02961 0.02377 -0.0747 0.7573 1.0000
1.750 0.4077 0.02973 0.02385 -0.0730 0.7535 1.0000
2.000 0.4412 0.02973 0.02381 -0.0740 0.7515 1.0000
2.250 0.4828 0.02968 0.02373 -0.0763 0.7504 1.0000
2.500 0.4453 0.03034 0.02439 -0.0663 0.7388 1.0000
2.750 0.4822 0.03034 0.02437 -0.0678 0.7373 1.0000
3.000 0.5210 0.03034 0.02437 -0.0696 0.7359 1.0000
3.250 0.5141 0.03116 0.02519 -0.0656 0.7250 1.0000
3.500 0.5533 0.03106 0.02510 -0.0673 0.7235 1.0000
3.750 0.5941 0.03092 0.02499 -0.0693 0.7225 1.0000
4.000 0.5947 0.03176 0.02584 -0.0665 0.7111 1.0000
4.250 0.6343 0.03156 0.02570 -0.0683 0.7097 1.0000
4.500 0.6768 0.03119 0.02538 -0.0703 0.7088 1.0000
4.750 0.6812 0.03199 0.02621 -0.0680 0.6974 1.0000
5.000 0.6981 0.03247 0.02674 -0.0672 0.6893 1.0000
5.250 0.7326 0.03219 0.02656 -0.0682 0.6855 1.0000
5.500 0.7738 0.03157 0.02602 -0.0698 0.6838 1.0000
5.750 0.7915 0.03186 0.02639 -0.0688 0.6747 1.0000
6.000 0.8335 0.03091 0.02555 -0.0703 0.6719 1.0000
6.250 0.8827 0.02938 0.02418 -0.0723 0.6704 1.0000
6.500 0.9443 0.02669 0.02168 -0.0753 0.6697 1.0000
6.750 1.0047 0.02358 0.01877 -0.0777 0.6662 1.0000
7.000 1.0571 0.02058 0.01594 -0.0793 0.6575 1.0000
7.250 1.0866 0.01892 0.01441 -0.0782 0.6437 1.0000
7.500 1.0933 0.01902 0.01461 -0.0751 0.6258 1.0000
7.750 1.1084 0.01893 0.01463 -0.0733 0.6016 1.0000
8.000 1.1601 0.01599 0.01101 -0.0732 0.4761 1.0000
8.250 1.1442 0.01791 0.01239 -0.0675 0.3973 1.0000
8.500 1.1270 0.02028 0.01431 -0.0626 0.3281 1.0000
8.750 1.1105 0.02288 0.01645 -0.0581 0.2565 1.0000
9.000 1.0952 0.02562 0.01866 -0.0541 0.1787 1.0000
9.250 1.0839 0.02831 0.02082 -0.0507 0.1101 1.0000
9.500 1.0797 0.03066 0.02286 -0.0479 0.0748 1.0000
9.750 1.0822 0.03260 0.02471 -0.0458 0.0591 1.0000
10.000 1.0874 0.03437 0.02648 -0.0441 0.0483 1.0000
10.250 1.0915 0.03631 0.02843 -0.0423 0.0402 1.0000
10.500 1.0954 0.03833 0.03043 -0.0405 0.0336 1.0000
10.750 1.1044 0.04011 0.03232 -0.0388 0.0291 1.0000
11.000 1.1135 0.04186 0.03406 -0.0376 0.0245 1.0000
11.250 1.1291 0.04361 0.03594 -0.0362 0.0218 1.0000
11.500 1.1508 0.04506 0.03752 -0.0353 0.0201 1.0000
11.750 1.1758 0.04669 0.03932 -0.0346 0.0188 1.0000
12.000 1.2013 0.04871 0.04155 -0.0341 0.0181 1.0000
12.250 1.2249 0.05136 0.04449 -0.0334 0.0177 1.0000
12.500 1.2427 0.05490 0.04842 -0.0324 0.0179 1.0000
12.750 1.2456 0.05947 0.05349 -0.0306 0.0185 1.0000
13.000 1.2387 0.06436 0.05881 -0.0286 0.0193 1.0000
13.250 1.2270 0.06924 0.06404 -0.0268 0.0200 1.0000
13.500 1.2121 0.07408 0.06917 -0.0254 0.0205 1.0000
13.750 1.1952 0.07898 0.07434 -0.0245 0.0208 1.0000
14.000 1.1760 0.08427 0.07987 -0.0241 0.0212 1.0000
14.250 1.1559 0.08977 0.08559 -0.0242 0.0214 1.0000
14.500 1.1353 0.09562 0.09164 -0.0251 0.0218 1.0000
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Polar data table (+)
Polar graphs
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