PW1211 (pw1211-pw) Xfoil prediction polar at RE=5,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: PW1211 (pw1211-pw) Reynolds number: 5,000,000 Max Cl/Cd: 114.18 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pw1211-pw-5000000.txt Download as CSV file: xf-pw1211-pw-5000000.csv |
XFOIL Version 6.96
Calculated polar for: PW1211
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 5.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.4884 0.03988 0.03840 -0.0072 1.0000 0.0020
-15.250 -1.4909 0.03616 0.03450 -0.0071 1.0000 0.0020
-15.000 -1.4846 0.03344 0.03163 -0.0066 1.0000 0.0021
-14.750 -1.4804 0.03005 0.02802 -0.0060 1.0000 0.0023
-14.500 -1.4656 0.02825 0.02612 -0.0054 1.0000 0.0025
-14.250 -1.4442 0.02754 0.02542 -0.0050 1.0000 0.0027
-14.000 -1.4205 0.02721 0.02512 -0.0046 1.0000 0.0028
-13.750 -1.3967 0.02686 0.02479 -0.0042 1.0000 0.0030
-13.500 -1.3717 0.02674 0.02470 -0.0038 1.0000 0.0031
-13.250 -1.3472 0.02649 0.02447 -0.0035 1.0000 0.0032
-13.000 -1.3219 0.02640 0.02441 -0.0031 1.0000 0.0033
-12.750 -1.2961 0.02640 0.02444 -0.0028 1.0000 0.0033
-12.500 -1.2705 0.02634 0.02441 -0.0025 1.0000 0.0034
-12.250 -1.2449 0.02626 0.02435 -0.0022 1.0000 0.0035
-12.000 -1.2190 0.02625 0.02437 -0.0019 1.0000 0.0035
-11.750 -1.1929 0.02628 0.02444 -0.0016 1.0000 0.0036
-11.500 -1.1669 0.02628 0.02446 -0.0014 1.0000 0.0036
-11.250 -1.1407 0.02631 0.02451 -0.0011 1.0000 0.0036
-11.000 -1.1146 0.02631 0.02454 -0.0009 1.0000 0.0037
-10.750 -1.0884 0.02633 0.02458 -0.0006 1.0000 0.0037
-10.500 -1.0619 0.02642 0.02470 -0.0004 1.0000 0.0037
-10.250 -1.0359 0.02636 0.02466 -0.0002 1.0000 0.0038
-10.000 -1.0101 0.02623 0.02453 0.0000 1.0000 0.0038
-9.750 -0.9842 0.02608 0.02439 0.0001 1.0000 0.0038
-9.500 -0.9580 0.02605 0.02437 0.0003 1.0000 0.0038
-9.250 -0.9326 0.02567 0.02397 0.0004 1.0000 0.0038
-9.000 -0.9074 0.02517 0.02344 0.0005 1.0000 0.0039
-8.750 -0.8823 0.02460 0.02283 0.0006 1.0000 0.0039
-8.500 -0.8570 0.02415 0.02235 0.0008 0.9759 0.0039
-8.250 -0.8364 0.02376 0.02186 0.0020 0.9438 0.0039
-8.000 -0.8327 0.01462 0.01160 0.0032 0.9228 0.0043
-7.750 -0.8081 0.01373 0.01055 0.0037 0.9046 0.0044
-7.500 -0.7820 0.01324 0.00995 0.0040 0.8879 0.0045
-7.250 -0.7553 0.01293 0.00958 0.0042 0.8737 0.0046
-7.000 -0.7282 0.01265 0.00924 0.0043 0.8610 0.0047
-6.750 -0.7012 0.01234 0.00886 0.0045 0.8484 0.0047
-6.500 -0.6742 0.01194 0.00838 0.0047 0.8349 0.0048
-6.250 -0.6473 0.01142 0.00775 0.0049 0.8201 0.0049
-6.000 -0.6204 0.01079 0.00700 0.0051 0.8040 0.0050
-5.750 -0.5935 0.01014 0.00623 0.0053 0.7880 0.0050
-5.500 -0.5663 0.00965 0.00563 0.0055 0.7733 0.0051
-5.250 -0.5383 0.00956 0.00550 0.0055 0.7600 0.0053
-5.000 -0.5104 0.00940 0.00530 0.0056 0.7471 0.0054
-4.750 -0.4830 0.00886 0.00466 0.0058 0.7342 0.0055
-4.500 -0.4559 0.00813 0.00379 0.0061 0.7205 0.0056
-4.000 -0.4005 0.00726 0.00272 0.0064 0.6900 0.0058
-3.750 -0.3724 0.00705 0.00244 0.0065 0.6737 0.0060
-3.500 -0.3441 0.00693 0.00227 0.0065 0.6557 0.0063
-3.250 -0.3157 0.00691 0.00222 0.0065 0.6377 0.0064
-3.000 -0.2872 0.00691 0.00219 0.0065 0.6203 0.0065
-2.750 -0.2593 0.00651 0.00168 0.0066 0.6050 0.0073
-2.500 -0.2310 0.00635 0.00145 0.0066 0.5880 0.0078
-2.250 -0.2026 0.00624 0.00128 0.0066 0.5702 0.0080
-2.000 -0.1741 0.00614 0.00114 0.0066 0.5546 0.0082
-1.750 -0.1456 0.00606 0.00100 0.0066 0.5380 0.0083
-1.500 -0.1171 0.00600 0.00087 0.0066 0.5200 0.0084
-1.250 -0.0885 0.00595 0.00077 0.0066 0.5011 0.0086
-1.000 -0.0599 0.00591 0.00068 0.0066 0.4863 0.0087
-0.750 -0.0313 0.00588 0.00061 0.0066 0.4708 0.0091
-0.500 -0.0027 0.00587 0.00054 0.0065 0.4521 0.0099
-0.250 0.0257 0.00575 0.00047 0.0064 0.4284 0.0448
0.250 0.0823 0.00546 0.00040 0.0063 0.3929 0.1621
0.500 0.1106 0.00531 0.00038 0.0062 0.3731 0.2380
0.750 0.1387 0.00516 0.00038 0.0060 0.3522 0.3228
1.000 0.1665 0.00488 0.00039 0.0059 0.3341 0.4561
1.250 0.1943 0.00467 0.00041 0.0058 0.3194 0.5645
1.500 0.2210 0.00424 0.00043 0.0059 0.3062 0.7493
1.750 0.2478 0.00400 0.00045 0.0062 0.2934 0.8556
2.000 0.2708 0.00380 0.00050 0.0075 0.2770 0.9600
2.250 0.3022 0.00390 0.00056 0.0068 0.2571 0.9891
2.500 0.3356 0.00405 0.00062 0.0056 0.2336 0.9961
2.750 0.3687 0.00417 0.00067 0.0044 0.2188 0.9990
3.000 0.3989 0.00427 0.00072 0.0040 0.2080 1.0000
3.250 0.4268 0.00439 0.00079 0.0040 0.1932 1.0000
3.500 0.4546 0.00455 0.00086 0.0040 0.1746 1.0000
3.750 0.4825 0.00469 0.00094 0.0040 0.1603 1.0000
4.000 0.5105 0.00486 0.00103 0.0040 0.1428 1.0000
4.250 0.5384 0.00507 0.00115 0.0039 0.1213 1.0000
4.500 0.5664 0.00523 0.00125 0.0039 0.1087 1.0000
4.750 0.5944 0.00540 0.00136 0.0038 0.0961 1.0000
5.000 0.6223 0.00560 0.00149 0.0038 0.0816 1.0000
5.250 0.6503 0.00581 0.00164 0.0037 0.0692 1.0000
5.500 0.6782 0.00602 0.00179 0.0036 0.0572 1.0000
5.750 0.7061 0.00625 0.00195 0.0035 0.0462 1.0000
6.000 0.7339 0.00649 0.00213 0.0035 0.0367 1.0000
6.250 0.7617 0.00674 0.00233 0.0034 0.0283 1.0000
6.500 0.7895 0.00693 0.00250 0.0033 0.0235 1.0000
6.750 0.8172 0.00720 0.00272 0.0032 0.0172 1.0000
7.000 0.8449 0.00740 0.00290 0.0031 0.0150 1.0000
7.250 0.8724 0.00774 0.00319 0.0030 0.0094 1.0000
7.500 0.8999 0.00799 0.00343 0.0030 0.0069 1.0000
7.750 0.9271 0.00849 0.00390 0.0029 0.0012 1.0000
8.000 0.9545 0.00875 0.00417 0.0028 0.0010 1.0000
8.250 0.9819 0.00903 0.00446 0.0027 0.0010 1.0000
8.500 1.0092 0.00932 0.00476 0.0027 0.0009 1.0000
8.750 1.0363 0.00963 0.00510 0.0026 0.0009 1.0000
9.000 1.0634 0.00995 0.00545 0.0026 0.0009 1.0000
9.250 1.0903 0.01030 0.00583 0.0025 0.0009 1.0000
9.500 1.1170 0.01067 0.00623 0.0025 0.0009 1.0000
9.750 1.1436 0.01108 0.00667 0.0024 0.0009 1.0000
10.000 1.1700 0.01151 0.00715 0.0024 0.0009 1.0000
10.250 1.1961 0.01198 0.00766 0.0024 0.0009 1.0000
10.500 1.2220 0.01249 0.00822 0.0024 0.0009 1.0000
10.750 1.2476 0.01304 0.00884 0.0024 0.0009 1.0000
11.000 1.2729 0.01365 0.00950 0.0024 0.0009 1.0000
11.250 1.2977 0.01430 0.01022 0.0024 0.0009 1.0000
11.500 1.3222 0.01498 0.01096 0.0025 0.0009 1.0000
11.750 1.3463 0.01569 0.01175 0.0025 0.0009 1.0000
12.000 1.3698 0.01648 0.01261 0.0026 0.0008 1.0000
12.250 1.3926 0.01736 0.01358 0.0027 0.0008 1.0000
12.500 1.4144 0.01835 0.01466 0.0029 0.0008 1.0000
12.750 1.4351 0.01945 0.01587 0.0030 0.0009 1.0000
13.000 1.4546 0.02066 0.01720 0.0033 0.0009 1.0000
13.250 1.4724 0.02201 0.01867 0.0036 0.0009 1.0000
13.500 1.4883 0.02352 0.02030 0.0039 0.0009 1.0000
13.750 1.5014 0.02523 0.02215 0.0042 0.0009 1.0000
14.000 1.5112 0.02715 0.02421 0.0046 0.0009 1.0000
14.250 1.5128 0.02959 0.02679 0.0048 0.0009 1.0000
14.500 1.5074 0.03256 0.02989 0.0043 0.0009 1.0000
14.750 1.4996 0.03664 0.03411 0.0022 0.0009 1.0000
15.000 1.4892 0.04181 0.03943 -0.0012 0.0009 1.0000
15.250 1.4712 0.04881 0.04658 -0.0061 0.0009 1.0000
15.500 1.4507 0.05659 0.05449 -0.0113 0.0009 1.0000
15.750 1.4246 0.06543 0.06346 -0.0168 0.0009 1.0000
16.000 1.3938 0.07509 0.07325 -0.0221 0.0009 1.0000
16.250 1.3581 0.08563 0.08390 -0.0276 0.0009 1.0000
16.500 1.3232 0.09606 0.09443 -0.0328 0.0009 1.0000
16.750 1.2853 0.10734 0.10581 -0.0384 0.0009 1.0000
17.000 1.2516 0.11810 0.11665 -0.0436 0.0009 1.0000
17.250 1.2174 0.12941 0.12804 -0.0492 0.0009 1.0000
17.500 1.1893 0.13984 0.13855 -0.0545 0.0009 1.0000
17.750 1.1603 0.15093 0.14971 -0.0602 0.0009 1.0000
18.000 1.1371 0.16113 0.15999 -0.0655 0.0009 1.0000
18.250 1.1194 0.17048 0.16939 -0.0705 0.0009 1.0000
18.500 1.0996 0.18078 0.17976 -0.0762 0.0009 1.0000
18.750 1.0904 0.18859 0.18761 -0.0806 0.0009 1.0000
19.000 1.0762 0.19851 0.19759 -0.0861 0.0010 1.0000
19.250 1.0614 0.20946 0.20861 -0.0922 0.0010 1.0000
19.500 1.0571 0.21691 0.21610 -0.0965 0.0010 1.0000
19.750 1.0425 0.22972 0.22898 -0.1033 0.0010 1.0000
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