74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: 74-130 WP2 (fx74130wp2-il) Reynolds number: 200,000 Max Cl/Cd: 75.31 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74130wp2-il-200000-n5.txt Download as CSV file: xf-fx74130wp2-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1209 0.08799 0.08369 -0.0904 0.7862 0.0268
-8.250 -0.1757 0.06756 0.06304 -0.1134 0.7803 0.0270
-7.750 -0.1824 0.06155 0.05682 -0.1136 0.7775 0.0271
-7.250 -0.1860 0.05115 0.04628 -0.1130 0.7747 0.0175
-7.000 -0.1836 0.04802 0.04304 -0.1125 0.7733 0.0166
-6.750 -0.1776 0.04474 0.03959 -0.1119 0.7718 0.0157
-6.500 -0.1696 0.04113 0.03572 -0.1110 0.7704 0.0148
-6.250 -0.1599 0.03676 0.03095 -0.1095 0.7689 0.0135
-6.000 -0.1460 0.03228 0.02585 -0.1075 0.7675 0.0124
-5.750 -0.1260 0.03036 0.02358 -0.1066 0.7663 0.0121
-5.500 -0.1067 0.02797 0.02080 -0.1057 0.7652 0.0121
-5.250 -0.0853 0.02591 0.01837 -0.1050 0.7644 0.0121
-5.000 -0.0626 0.02391 0.01602 -0.1044 0.7635 0.0123
-4.750 -0.0394 0.02243 0.01433 -0.1039 0.7623 0.0126
-4.500 -0.0155 0.02146 0.01325 -0.1036 0.7609 0.0135
-4.250 0.0091 0.02088 0.01256 -0.1034 0.7595 0.0151
-4.000 0.0342 0.02016 0.01170 -0.1031 0.7580 0.0165
-3.750 0.0589 0.01926 0.01070 -0.1026 0.7566 0.0169
-3.500 0.0833 0.01852 0.00989 -0.1021 0.7553 0.0173
-3.250 0.1076 0.01791 0.00921 -0.1016 0.7542 0.0179
-3.000 0.1317 0.01730 0.00852 -0.1012 0.7532 0.0189
-2.750 0.1566 0.01684 0.00799 -0.1010 0.7522 0.0212
-2.500 0.1826 0.01654 0.00760 -0.1008 0.7513 0.0259
-2.250 0.2082 0.01611 0.00724 -0.1007 0.7503 0.0528
-2.000 0.2271 0.01482 0.00708 -0.1005 0.7488 0.3363
-1.750 0.2316 0.01408 0.00796 -0.0954 0.7468 0.7566
-1.500 0.2522 0.01454 0.00838 -0.0936 0.7451 0.8105
-1.250 0.2669 0.01504 0.00887 -0.0900 0.7434 0.8473
-1.000 0.2801 0.01534 0.00917 -0.0860 0.7417 0.8694
-0.750 0.3007 0.01545 0.00922 -0.0842 0.7402 0.8807
-0.500 0.3253 0.01554 0.00920 -0.0838 0.7390 0.8879
-0.250 0.3505 0.01560 0.00918 -0.0834 0.7380 0.8917
0.000 0.3768 0.01565 0.00916 -0.0833 0.7371 0.8950
0.250 0.4043 0.01570 0.00912 -0.0835 0.7362 0.8981
0.500 0.4242 0.01604 0.00948 -0.0828 0.7330 0.9019
0.750 0.4463 0.01628 0.00970 -0.0823 0.7307 0.9045
1.000 0.4705 0.01642 0.00983 -0.0820 0.7286 0.9068
1.250 0.4962 0.01653 0.00992 -0.0820 0.7269 0.9091
1.500 0.5233 0.01662 0.00999 -0.0822 0.7255 0.9111
1.750 0.5516 0.01667 0.01001 -0.0827 0.7243 0.9131
2.000 0.5808 0.01669 0.01002 -0.0833 0.7232 0.9149
2.500 0.6202 0.01736 0.01080 -0.0816 0.7158 0.9195
2.750 0.6455 0.01747 0.01093 -0.0815 0.7135 0.9216
3.000 0.6735 0.01751 0.01099 -0.0819 0.7118 0.9233
3.250 0.7028 0.01750 0.01103 -0.0824 0.7104 0.9248
3.500 0.7333 0.01745 0.01101 -0.0832 0.7093 0.9263
4.000 0.7696 0.01812 0.01184 -0.0809 0.6996 0.9324
4.250 0.7998 0.01799 0.01177 -0.0815 0.6977 0.9340
4.500 0.8325 0.01774 0.01160 -0.0824 0.6962 0.9354
5.000 0.8734 0.01800 0.01207 -0.0806 0.6854 0.9421
5.500 0.9224 0.01771 0.01203 -0.0797 0.6746 0.9493
5.750 0.9595 0.01685 0.01125 -0.0809 0.6698 0.9509
6.000 0.9758 0.01680 0.01135 -0.0791 0.6590 0.9576
6.250 0.9968 0.01659 0.01127 -0.0781 0.6464 0.9654
6.500 1.0196 0.01630 0.01112 -0.0775 0.6299 0.9794
6.750 1.0298 0.01658 0.01148 -0.0751 0.6074 1.0000
7.000 1.0829 0.01438 0.00878 -0.0769 0.5158 1.0000
7.250 1.0774 0.01549 0.00935 -0.0718 0.4383 1.0000
7.500 1.0676 0.01720 0.01070 -0.0672 0.3782 1.0000
7.750 1.0602 0.01907 0.01227 -0.0635 0.3231 1.0000
8.000 1.0570 0.02088 0.01382 -0.0605 0.2727 1.0000
8.250 1.0549 0.02272 0.01538 -0.0577 0.2216 1.0000
8.500 1.0546 0.02454 0.01691 -0.0552 0.1720 1.0000
8.750 1.0567 0.02626 0.01841 -0.0531 0.1266 1.0000
9.000 1.0611 0.02790 0.01983 -0.0512 0.0905 1.0000
9.250 1.0684 0.02936 0.02117 -0.0496 0.0664 1.0000
9.500 1.0770 0.03078 0.02252 -0.0482 0.0498 1.0000
9.750 1.0867 0.03214 0.02388 -0.0469 0.0397 1.0000
10.000 1.0958 0.03357 0.02529 -0.0456 0.0317 1.0000
10.250 1.1067 0.03488 0.02665 -0.0445 0.0256 1.0000
10.500 1.1163 0.03634 0.02816 -0.0434 0.0211 1.0000
10.750 1.1260 0.03781 0.02973 -0.0422 0.0180 1.0000
11.000 1.1313 0.03974 0.03174 -0.0408 0.0150 1.0000
11.250 1.1427 0.04113 0.03325 -0.0399 0.0127 1.0000
11.500 1.1524 0.04270 0.03490 -0.0390 0.0112 1.0000
11.750 1.1578 0.04475 0.03702 -0.0378 0.0101 1.0000
12.000 1.1633 0.04684 0.03924 -0.0366 0.0095 1.0000
12.250 1.1710 0.04880 0.04135 -0.0356 0.0089 1.0000
12.500 1.1788 0.05079 0.04349 -0.0346 0.0085 1.0000
12.750 1.1866 0.05288 0.04573 -0.0337 0.0080 1.0000
13.000 1.1946 0.05500 0.04800 -0.0328 0.0077 1.0000
13.250 1.2023 0.05721 0.05035 -0.0320 0.0074 1.0000
13.500 1.2093 0.05955 0.05285 -0.0313 0.0071 1.0000
13.750 1.2153 0.06205 0.05553 -0.0307 0.0070 1.0000
14.000 1.2195 0.06481 0.05850 -0.0301 0.0068 1.0000
14.250 1.2220 0.06785 0.06173 -0.0297 0.0066 1.0000
14.500 1.2226 0.07117 0.06527 -0.0293 0.0065 1.0000
14.750 1.2205 0.07496 0.06927 -0.0291 0.0064 1.0000
15.000 1.2156 0.07919 0.07374 -0.0291 0.0063 1.0000
15.250 1.2078 0.08391 0.07872 -0.0295 0.0063 1.0000
15.500 1.1969 0.08921 0.08427 -0.0303 0.0062 1.0000
15.750 1.1844 0.09492 0.09023 -0.0316 0.0062 1.0000
16.000 1.1714 0.10091 0.09645 -0.0335 0.0061 1.0000
16.250 1.1575 0.10734 0.10313 -0.0361 0.0061 1.0000
16.500 1.1427 0.11428 0.11030 -0.0392 0.0061 1.0000
16.750 1.1274 0.12172 0.11795 -0.0431 0.0061 1.0000
17.000 1.1115 0.12977 0.12621 -0.0477 0.0061 1.0000
17.250 1.0954 0.13835 0.13496 -0.0529 0.0061 1.0000
17.500 0.8263 0.15639 0.15401 -0.0625 0.0077 1.0000
|
Polar data table (+)
Polar graphs
<< Back to 74-130 WP2 (fx74130wp2-il)