WASP (smoothed) (waspsm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WASP (smoothed) (waspsm-il) Reynolds number: 50,000 Max Cl/Cd: 37.55 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-waspsm-il-50000-n5.txt Download as CSV file: xf-waspsm-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4301 0.09727 0.09020 -0.0288 1.0000 0.0622
-8.250 -0.4231 0.09379 0.08675 -0.0281 1.0000 0.0611
-8.000 -0.4213 0.09028 0.08331 -0.0285 1.0000 0.0599
-7.750 -0.4221 0.08658 0.07970 -0.0296 1.0000 0.0587
-7.500 -0.4220 0.08245 0.07564 -0.0318 1.0000 0.0576
-7.250 -0.4219 0.07798 0.07123 -0.0345 1.0000 0.0565
-7.000 -0.4214 0.07309 0.06637 -0.0376 1.0000 0.0554
-6.750 -0.4202 0.06778 0.06105 -0.0407 1.0000 0.0544
-6.500 -0.4175 0.06249 0.05567 -0.0433 1.0000 0.0538
-6.250 -0.4119 0.05810 0.05115 -0.0446 1.0000 0.0544
-6.000 -0.4043 0.05406 0.04695 -0.0455 1.0000 0.0557
-5.750 -0.3952 0.04995 0.04257 -0.0461 1.0000 0.0570
-5.500 -0.3842 0.04584 0.03809 -0.0464 1.0000 0.0581
-5.250 -0.3708 0.04200 0.03382 -0.0463 1.0000 0.0587
-5.000 -0.3551 0.03850 0.02981 -0.0458 1.0000 0.0596
-4.750 -0.3371 0.03539 0.02602 -0.0451 1.0000 0.0618
-4.500 -0.3189 0.03338 0.02382 -0.0443 1.0000 0.0652
-4.250 -0.2992 0.03168 0.02188 -0.0434 1.0000 0.0687
-4.000 -0.2774 0.02971 0.01950 -0.0425 1.0000 0.0717
-3.750 -0.2547 0.02808 0.01741 -0.0417 1.0000 0.0766
-3.500 -0.2336 0.02701 0.01631 -0.0409 1.0000 0.0830
-3.250 -0.2099 0.02580 0.01474 -0.0401 1.0000 0.0891
-3.000 -0.1873 0.02493 0.01390 -0.0395 1.0000 0.0985
-2.750 -0.1637 0.02409 0.01296 -0.0390 1.0000 0.1090
-2.500 -0.1360 0.02340 0.01219 -0.0393 0.9982 0.1255
-2.250 -0.0929 0.02256 0.01132 -0.0426 0.9889 0.1559
-2.000 -0.0504 0.02169 0.01064 -0.0460 0.9789 0.2111
-1.750 -0.0090 0.02071 0.01022 -0.0492 0.9688 0.3252
-1.500 0.0277 0.01964 0.01006 -0.0510 0.9584 0.5335
-1.250 0.0845 0.01834 0.00967 -0.0553 0.9503 1.0000
-1.000 0.1286 0.01845 0.00934 -0.0587 0.9374 1.0000
-0.750 0.1723 0.01852 0.00909 -0.0619 0.9244 1.0000
-0.500 0.2135 0.01859 0.00889 -0.0644 0.9101 1.0000
-0.250 0.2526 0.01863 0.00870 -0.0665 0.8950 1.0000
0.000 0.2883 0.01868 0.00856 -0.0678 0.8785 1.0000
0.250 0.3225 0.01872 0.00844 -0.0688 0.8613 1.0000
0.500 0.3561 0.01875 0.00833 -0.0695 0.8438 1.0000
0.750 0.3893 0.01878 0.00823 -0.0701 0.8262 1.0000
1.000 0.4219 0.01880 0.00813 -0.0705 0.8085 1.0000
1.250 0.4541 0.01883 0.00804 -0.0707 0.7908 1.0000
1.500 0.4819 0.01895 0.00807 -0.0702 0.7704 1.0000
1.750 0.5106 0.01905 0.00809 -0.0698 0.7508 1.0000
2.000 0.5396 0.01916 0.00809 -0.0694 0.7318 1.0000
2.250 0.5659 0.01935 0.00820 -0.0687 0.7113 1.0000
2.500 0.5927 0.01955 0.00832 -0.0680 0.6911 1.0000
2.750 0.6200 0.01975 0.00845 -0.0674 0.6718 1.0000
3.000 0.6454 0.02002 0.00867 -0.0665 0.6513 1.0000
3.250 0.6710 0.02030 0.00889 -0.0657 0.6313 1.0000
3.500 0.6970 0.02058 0.00910 -0.0650 0.6123 1.0000
3.750 0.7219 0.02091 0.00943 -0.0641 0.5926 1.0000
4.000 0.7465 0.02127 0.00976 -0.0632 0.5732 1.0000
4.250 0.7714 0.02164 0.01009 -0.0624 0.5545 1.0000
4.500 0.7964 0.02201 0.01046 -0.0615 0.5364 1.0000
4.750 0.8199 0.02246 0.01093 -0.0606 0.5174 1.0000
5.000 0.8436 0.02292 0.01140 -0.0596 0.4990 1.0000
5.250 0.8673 0.02339 0.01189 -0.0587 0.4813 1.0000
5.500 0.8909 0.02388 0.01243 -0.0578 0.4639 1.0000
5.750 0.9144 0.02439 0.01296 -0.0568 0.4472 1.0000
6.000 0.9372 0.02496 0.01359 -0.0558 0.4303 1.0000
6.250 0.9595 0.02556 0.01427 -0.0548 0.4134 1.0000
6.500 0.9818 0.02619 0.01502 -0.0538 0.3972 1.0000
6.750 1.0038 0.02684 0.01577 -0.0528 0.3814 1.0000
7.000 1.0255 0.02753 0.01656 -0.0517 0.3660 1.0000
7.250 1.0470 0.02826 0.01741 -0.0506 0.3512 1.0000
7.500 1.0680 0.02902 0.01832 -0.0495 0.3364 1.0000
7.750 1.0888 0.02982 0.01925 -0.0484 0.3224 1.0000
8.000 1.1089 0.03065 0.02022 -0.0471 0.3083 1.0000
8.250 1.1285 0.03151 0.02123 -0.0459 0.2944 1.0000
8.500 1.1468 0.03238 0.02226 -0.0444 0.2798 1.0000
8.750 1.1625 0.03322 0.02328 -0.0427 0.2632 1.0000
9.000 1.1748 0.03395 0.02410 -0.0406 0.2441 1.0000
9.250 1.1843 0.03476 0.02496 -0.0382 0.2238 1.0000
9.500 1.1919 0.03578 0.02612 -0.0358 0.2031 1.0000
9.750 1.1978 0.03693 0.02730 -0.0334 0.1839 1.0000
10.000 1.2013 0.03840 0.02891 -0.0309 0.1627 1.0000
10.250 1.2006 0.04009 0.03061 -0.0281 0.1440 1.0000
10.750 1.1926 0.04459 0.03517 -0.0231 0.1109 1.0000
11.000 1.1867 0.04737 0.03794 -0.0214 0.0990 1.0000
11.250 1.1800 0.05044 0.04099 -0.0202 0.0901 1.0000
11.500 1.1753 0.05370 0.04437 -0.0194 0.0820 1.0000
11.750 1.1687 0.05719 0.04782 -0.0190 0.0772 1.0000
12.000 1.1647 0.06078 0.05163 -0.0188 0.0717 1.0000
12.250 1.1589 0.06453 0.05543 -0.0190 0.0677 1.0000
12.500 1.1537 0.06842 0.05939 -0.0193 0.0643 1.0000
12.750 1.1491 0.07251 0.06372 -0.0198 0.0611 1.0000
13.000 1.1445 0.07661 0.06798 -0.0203 0.0587 1.0000
13.250 1.1402 0.08065 0.07210 -0.0209 0.0566 1.0000
13.500 1.1375 0.08438 0.07579 -0.0212 0.0545 1.0000
13.750 1.1276 0.08988 0.08161 -0.0230 0.0532 1.0000
14.000 1.1156 0.09589 0.08789 -0.0253 0.0521 1.0000
14.250 1.1014 0.10252 0.09477 -0.0282 0.0513 1.0000
14.500 1.0846 0.11001 0.10249 -0.0318 0.0509 1.0000
14.750 1.0638 0.11886 0.11154 -0.0364 0.0509 1.0000
15.000 1.0377 0.12979 0.12265 -0.0425 0.0516 1.0000
15.250 1.0093 0.14239 0.13532 -0.0495 0.0525 1.0000
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Polar data table (+)
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