WASP (smoothed) (waspsm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: WASP (smoothed) (waspsm-il) Reynolds number: 50,000 Max Cl/Cd: 31.08 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-waspsm-il-50000.txt Download as CSV file: xf-waspsm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WASP (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4277 0.11372 0.10676 -0.0145 1.0000 0.2078
-8.500 -0.4008 0.10746 0.10047 -0.0124 1.0000 0.2169
-8.250 -0.4243 0.10763 0.10082 -0.0150 1.0000 0.2230
-8.000 -0.3966 0.10161 0.09474 -0.0128 1.0000 0.2338
-7.750 -0.4006 0.09897 0.09220 -0.0133 1.0000 0.2410
-7.500 -0.4040 0.09692 0.09025 -0.0131 1.0000 0.2520
-7.250 -0.3905 0.09282 0.08618 -0.0119 1.0000 0.2632
-7.000 -0.3896 0.08997 0.08342 -0.0109 1.0000 0.2752
-6.750 -0.3934 0.08752 0.08109 -0.0099 1.0000 0.2880
-6.500 -0.3906 0.08471 0.07837 -0.0085 1.0000 0.3040
-6.250 -0.3876 0.08191 0.07566 -0.0071 1.0000 0.3206
-6.000 -0.3856 0.07922 0.07305 -0.0055 1.0000 0.3376
-5.750 -0.3874 0.07686 0.07080 -0.0041 1.0000 0.3566
-5.500 -0.3915 0.07450 0.06856 -0.0027 1.0000 0.3766
-5.250 -0.3805 0.07126 0.06535 0.0006 1.0000 0.3970
-5.000 -0.3808 0.06891 0.06310 0.0038 1.0000 0.4246
-4.750 -0.3741 0.06634 0.06060 0.0084 1.0000 0.4590
-4.500 -0.3386 0.04685 0.03954 -0.0402 1.0000 0.1610
-4.250 -0.3213 0.04310 0.03554 -0.0403 1.0000 0.1570
-4.000 -0.3004 0.03893 0.03077 -0.0411 1.0000 0.1515
-3.750 -0.2769 0.03554 0.02656 -0.0412 1.0000 0.1473
-3.500 -0.2540 0.03284 0.02335 -0.0408 1.0000 0.1486
-3.250 -0.2330 0.03105 0.02155 -0.0401 1.0000 0.1574
-3.000 -0.2075 0.02905 0.01893 -0.0396 1.0000 0.1634
-2.750 -0.1839 0.02753 0.01731 -0.0391 1.0000 0.1752
-2.500 -0.1589 0.02619 0.01577 -0.0386 1.0000 0.1912
-2.250 -0.1329 0.02495 0.01449 -0.0384 1.0000 0.2129
-2.000 -0.1078 0.02388 0.01344 -0.0379 1.0000 0.2446
-1.750 -0.0789 0.02281 0.01256 -0.0382 1.0000 0.3053
-1.500 -0.0491 0.02112 0.01186 -0.0383 1.0000 0.4688
-1.250 -0.0170 0.01892 0.01099 -0.0377 1.0000 1.0000
-1.000 0.0038 0.01936 0.01096 -0.0376 1.0000 1.0000
-0.750 0.0234 0.01987 0.01112 -0.0373 1.0000 1.0000
-0.500 0.0422 0.02045 0.01142 -0.0371 1.0000 1.0000
-0.250 0.0603 0.02111 0.01183 -0.0370 1.0000 1.0000
0.000 0.0779 0.02186 0.01238 -0.0370 1.0000 1.0000
0.250 0.1210 0.02283 0.01311 -0.0418 0.9897 1.0000
0.500 0.1821 0.02376 0.01379 -0.0494 0.9699 1.0000
0.750 0.2416 0.02458 0.01442 -0.0564 0.9502 1.0000
1.000 0.2946 0.02523 0.01495 -0.0619 0.9287 1.0000
1.250 0.3510 0.02572 0.01535 -0.0676 0.9088 1.0000
1.500 0.3939 0.02614 0.01573 -0.0707 0.8864 1.0000
1.750 0.4476 0.02629 0.01586 -0.0751 0.8670 1.0000
2.000 0.4909 0.02649 0.01605 -0.0776 0.8463 1.0000
2.250 0.5321 0.02658 0.01616 -0.0793 0.8258 1.0000
2.500 0.5764 0.02644 0.01604 -0.0811 0.8072 1.0000
2.750 0.6086 0.02662 0.01625 -0.0810 0.7863 1.0000
3.000 0.6423 0.02666 0.01631 -0.0809 0.7660 1.0000
3.250 0.6783 0.02654 0.01620 -0.0808 0.7472 1.0000
3.500 0.7045 0.02685 0.01654 -0.0796 0.7259 1.0000
3.750 0.7334 0.02701 0.01674 -0.0786 0.7055 1.0000
4.000 0.7650 0.02699 0.01672 -0.0776 0.6866 1.0000
4.250 0.7871 0.02754 0.01732 -0.0760 0.6647 1.0000
4.500 0.8142 0.02779 0.01761 -0.0747 0.6446 1.0000
4.750 0.8421 0.02801 0.01783 -0.0734 0.6251 1.0000
5.000 0.8630 0.02872 0.01861 -0.0718 0.6036 1.0000
5.250 0.8893 0.02909 0.01899 -0.0704 0.5839 1.0000
5.500 0.9139 0.02964 0.01960 -0.0690 0.5643 1.0000
5.750 0.9347 0.03049 0.02055 -0.0675 0.5439 1.0000
6.000 0.9591 0.03111 0.02120 -0.0661 0.5248 1.0000
6.250 0.9852 0.03170 0.02179 -0.0649 0.5067 1.0000
6.500 1.0031 0.03291 0.02319 -0.0633 0.4875 1.0000
6.750 1.0234 0.03402 0.02443 -0.0618 0.4695 1.0000
7.000 1.0449 0.03505 0.02556 -0.0604 0.4521 1.0000
7.250 1.0664 0.03614 0.02676 -0.0590 0.4356 1.0000
7.500 1.0879 0.03724 0.02797 -0.0576 0.4193 1.0000
7.750 1.1090 0.03841 0.02930 -0.0562 0.4035 1.0000
8.000 1.1311 0.03947 0.03046 -0.0548 0.3874 1.0000
8.250 1.1470 0.04095 0.03214 -0.0530 0.3710 1.0000
8.500 1.1604 0.04239 0.03382 -0.0509 0.3530 1.0000
8.750 1.1904 0.04162 0.03296 -0.0492 0.3287 1.0000
9.000 1.2037 0.04200 0.03349 -0.0465 0.3037 1.0000
9.250 1.2224 0.04160 0.03302 -0.0439 0.2748 1.0000
9.500 1.2419 0.04094 0.03201 -0.0413 0.2403 1.0000
9.750 1.2448 0.04213 0.03324 -0.0375 0.2077 1.0000
10.000 1.2492 0.04378 0.03476 -0.0340 0.1774 1.0000
10.250 1.2577 0.04564 0.03640 -0.0313 0.1540 1.0000
10.500 1.2631 0.04840 0.03930 -0.0287 0.1390 1.0000
10.750 1.2712 0.05099 0.04191 -0.0265 0.1268 1.0000
11.000 1.2715 0.05399 0.04523 -0.0238 0.1188 1.0000
11.250 1.2759 0.05760 0.04900 -0.0219 0.1132 1.0000
11.500 1.2629 0.06158 0.05343 -0.0189 0.1107 1.0000
11.750 1.2471 0.06541 0.05756 -0.0160 0.1087 1.0000
12.000 1.2284 0.06954 0.06195 -0.0139 0.1075 1.0000
12.250 1.2160 0.07352 0.06609 -0.0128 0.1054 1.0000
12.500 1.1998 0.07811 0.07083 -0.0124 0.1041 1.0000
12.750 1.1843 0.08315 0.07598 -0.0127 0.1030 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WASP (smoothed) (waspsm-il)