PW106 (pw106-pw) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: PW106 (pw106-pw) Reynolds number: 1,000,000 Max Cl/Cd: 84.92 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pw106-pw-1000000.txt Download as CSV file: xf-pw106-pw-1000000.csv |
XFOIL Version 6.96
Calculated polar for: PW106
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-20.000 -0.8750 0.26807 0.26641 0.1108 1.0000 0.0061
-19.750 -0.8653 0.26506 0.26340 0.1087 1.0000 0.0062
-19.500 -0.8559 0.26198 0.26032 0.1065 1.0000 0.0063
-19.250 -0.8465 0.25890 0.25724 0.1043 1.0000 0.0064
-19.000 -0.8372 0.25578 0.25412 0.1022 1.0000 0.0065
-18.750 -0.8280 0.25263 0.25098 0.1001 1.0000 0.0066
-18.500 -0.8188 0.24945 0.24780 0.0980 1.0000 0.0066
-18.250 -0.8097 0.24624 0.24459 0.0959 1.0000 0.0066
-18.000 -0.8006 0.24300 0.24135 0.0938 1.0000 0.0067
-17.750 -0.7915 0.23972 0.23807 0.0918 1.0000 0.0067
-17.500 -0.7826 0.23642 0.23478 0.0897 1.0000 0.0067
-17.250 -0.7737 0.23311 0.23147 0.0877 1.0000 0.0068
-17.000 -0.7649 0.22977 0.22813 0.0857 1.0000 0.0068
-16.750 -0.7561 0.22638 0.22474 0.0837 1.0000 0.0068
-16.500 -0.7474 0.22294 0.22130 0.0817 1.0000 0.0068
-16.250 -0.7387 0.21948 0.21785 0.0798 1.0000 0.0068
-16.000 -0.7301 0.21600 0.21437 0.0778 1.0000 0.0068
-15.750 -0.7217 0.21248 0.21086 0.0759 1.0000 0.0068
-15.500 -0.7134 0.20892 0.20730 0.0741 1.0000 0.0068
-15.250 -0.7052 0.20533 0.20370 0.0722 1.0000 0.0069
-15.000 -0.6972 0.20173 0.20010 0.0704 1.0000 0.0069
-14.750 -0.6894 0.19809 0.19646 0.0686 1.0000 0.0069
-14.500 -0.6817 0.19443 0.19281 0.0668 1.0000 0.0069
-14.250 -0.6741 0.19072 0.18910 0.0650 1.0000 0.0069
-14.000 -0.6668 0.18694 0.18533 0.0633 1.0000 0.0069
-13.750 -0.6597 0.18316 0.18155 0.0615 1.0000 0.0069
-13.500 -0.6529 0.17930 0.17771 0.0599 1.0000 0.0068
-13.250 -0.6465 0.17541 0.17381 0.0582 1.0000 0.0068
-13.000 -0.6407 0.17134 0.16975 0.0566 1.0000 0.0067
-12.750 -0.6356 0.16706 0.16548 0.0549 1.0000 0.0066
-12.500 -0.6348 0.16182 0.16025 0.0534 1.0000 0.0058
-12.250 -0.6317 0.15742 0.15586 0.0518 1.0000 0.0051
-12.000 -0.6282 0.15303 0.15147 0.0501 1.0000 0.0046
-11.750 -0.6249 0.14848 0.14693 0.0484 1.0000 0.0041
-11.500 -0.6221 0.14385 0.14232 0.0467 1.0000 0.0038
-11.250 -0.6206 0.13883 0.13731 0.0448 1.0000 0.0034
-11.000 -0.6207 0.13331 0.13180 0.0427 1.0000 0.0031
-10.750 -0.6241 0.12690 0.12540 0.0403 1.0000 0.0028
-10.500 -0.6295 0.12008 0.11860 0.0376 1.0000 0.0026
-10.250 -0.6345 0.11373 0.11226 0.0349 1.0000 0.0025
-10.000 -0.6377 0.10807 0.10662 0.0323 1.0000 0.0025
-9.750 -0.6425 0.10210 0.10067 0.0293 1.0000 0.0024
-9.500 -0.6476 0.09613 0.09473 0.0260 1.0000 0.0024
-9.250 -0.6556 0.08953 0.08815 0.0218 1.0000 0.0024
-9.000 -0.8295 0.02670 0.02373 -0.0144 1.0000 0.0025
-8.750 -0.8091 0.02474 0.02153 -0.0141 1.0000 0.0028
-8.500 -0.8031 0.01780 0.01348 -0.0125 1.0000 0.0027
-8.250 -0.7828 0.01525 0.01041 -0.0117 1.0000 0.0027
-8.000 -0.7583 0.01402 0.00891 -0.0112 1.0000 0.0026
-7.750 -0.7325 0.01319 0.00790 -0.0109 1.0000 0.0026
-7.500 -0.7061 0.01254 0.00712 -0.0106 1.0000 0.0026
-7.250 -0.6792 0.01200 0.00647 -0.0104 1.0000 0.0025
-7.000 -0.6519 0.01153 0.00588 -0.0103 1.0000 0.0026
-6.750 -0.6244 0.01114 0.00542 -0.0102 1.0000 0.0026
-6.500 -0.5967 0.01077 0.00501 -0.0102 1.0000 0.0026
-6.250 -0.5681 0.01044 0.00464 -0.0103 0.9958 0.0027
-6.000 -0.5356 0.01016 0.00432 -0.0112 0.9738 0.0027
-5.750 -0.5104 0.00996 0.00406 -0.0104 0.9513 0.0028
-5.500 -0.4873 0.00978 0.00382 -0.0091 0.9293 0.0028
-5.250 -0.4629 0.00961 0.00357 -0.0081 0.9085 0.0028
-4.750 -0.4114 0.00930 0.00312 -0.0067 0.8671 0.0030
-4.500 -0.3846 0.00916 0.00287 -0.0063 0.8466 0.0030
-4.250 -0.3575 0.00903 0.00267 -0.0059 0.8258 0.0031
-4.000 -0.3301 0.00892 0.00249 -0.0057 0.8054 0.0032
-3.750 -0.3025 0.00881 0.00233 -0.0055 0.7848 0.0032
-3.500 -0.2747 0.00872 0.00220 -0.0053 0.7649 0.0034
-3.250 -0.2468 0.00865 0.00210 -0.0052 0.7454 0.0037
-3.000 -0.2187 0.00860 0.00203 -0.0052 0.7270 0.0039
-2.750 -0.1906 0.00858 0.00202 -0.0052 0.7088 0.0043
-2.500 -0.1623 0.00869 0.00219 -0.0052 0.6912 0.0050
-2.250 -0.1338 0.00893 0.00253 -0.0055 0.6736 0.0059
-1.750 -0.0768 0.00921 0.00285 -0.0057 0.6402 0.0075
-1.500 -0.0494 0.00871 0.00223 -0.0055 0.6249 0.0078
-1.250 -0.0216 0.00830 0.00167 -0.0052 0.6098 0.0091
-1.000 0.0066 0.00813 0.00140 -0.0051 0.5945 0.0112
-0.750 0.0351 0.00805 0.00124 -0.0051 0.5796 0.0107
-0.500 0.0636 0.00801 0.00111 -0.0051 0.5648 0.0105
-0.250 0.0921 0.00798 0.00100 -0.0050 0.5502 0.0105
0.000 0.1206 0.00797 0.00092 -0.0050 0.5356 0.0110
0.500 0.1756 0.00733 0.00087 -0.0051 0.5071 0.2210
0.750 0.2007 0.00651 0.00085 -0.0050 0.4935 0.4956
1.000 0.2212 0.00550 0.00088 -0.0036 0.4805 0.8168
1.250 0.2823 0.00533 0.00110 -0.0100 0.4617 0.9988
1.500 0.3137 0.00542 0.00111 -0.0108 0.4468 1.0000
1.750 0.3408 0.00550 0.00112 -0.0106 0.4331 1.0000
2.000 0.3678 0.00560 0.00114 -0.0105 0.4188 1.0000
2.250 0.3948 0.00570 0.00117 -0.0103 0.4049 1.0000
2.500 0.4217 0.00581 0.00122 -0.0101 0.3905 1.0000
3.000 0.4753 0.00604 0.00132 -0.0097 0.3619 1.0000
3.250 0.5022 0.00617 0.00139 -0.0095 0.3480 1.0000
3.500 0.5290 0.00630 0.00146 -0.0093 0.3352 1.0000
3.750 0.5554 0.00654 0.00155 -0.0092 0.3033 1.0000
4.000 0.5807 0.00712 0.00174 -0.0091 0.2289 1.0000
4.250 0.6061 0.00765 0.00195 -0.0090 0.1714 1.0000
4.500 0.6304 0.00846 0.00233 -0.0088 0.0951 1.0000
4.750 0.6537 0.00962 0.00301 -0.0085 0.0024 1.0000
5.000 0.6789 0.01028 0.00370 -0.0081 0.0022 1.0000
5.250 0.7033 0.01109 0.00448 -0.0077 0.0021 1.0000
5.750 0.7579 0.01103 0.00431 -0.0076 0.0021 1.0000
6.250 0.8130 0.01091 0.00423 -0.0076 0.0019 1.0000
6.500 0.8396 0.01112 0.00447 -0.0075 0.0019 1.0000
6.750 0.8662 0.01135 0.00474 -0.0074 0.0020 1.0000
7.000 0.8930 0.01155 0.00508 -0.0073 0.0020 1.0000
7.250 0.9196 0.01180 0.00535 -0.0072 0.0021 1.0000
7.500 0.9460 0.01209 0.00566 -0.0071 0.0022 1.0000
7.750 0.9722 0.01242 0.00604 -0.0070 0.0023 1.0000
8.000 0.9982 0.01279 0.00646 -0.0068 0.0024 1.0000
8.250 1.0240 0.01320 0.00695 -0.0066 0.0025 1.0000
8.500 1.0494 0.01368 0.00753 -0.0064 0.0026 1.0000
8.750 1.0743 0.01422 0.00818 -0.0061 0.0027 1.0000
9.000 1.0987 0.01483 0.00889 -0.0058 0.0029 1.0000
9.250 1.1226 0.01550 0.00966 -0.0054 0.0031 1.0000
9.500 1.1460 0.01623 0.01049 -0.0051 0.0034 1.0000
9.750 1.1682 0.01710 0.01154 -0.0046 0.0035 1.0000
10.000 1.1896 0.01805 0.01261 -0.0041 0.0038 1.0000
10.250 1.2092 0.01919 0.01391 -0.0034 0.0042 1.0000
10.500 1.2255 0.02072 0.01565 -0.0024 0.0046 1.0000
10.750 1.2359 0.02290 0.01808 -0.0008 0.0052 1.0000
11.000 1.2409 0.02558 0.02101 0.0011 0.0058 1.0000
11.250 1.2411 0.02867 0.02435 0.0032 0.0064 1.0000
11.500 1.2349 0.03189 0.02780 0.0055 0.0069 1.0000
11.750 1.2240 0.03590 0.03205 0.0070 0.0074 1.0000
12.000 1.2080 0.04083 0.03724 0.0074 0.0077 1.0000
15.000 1.0193 0.12189 0.12003 -0.0362 0.0080 1.0000
15.250 1.0107 0.12903 0.12724 -0.0402 0.0079 1.0000
15.500 1.0024 0.13626 0.13453 -0.0442 0.0077 1.0000
15.750 0.9918 0.14427 0.14260 -0.0485 0.0076 1.0000
16.000 0.9816 0.15243 0.15081 -0.0528 0.0074 1.0000
16.250 0.9716 0.16084 0.15927 -0.0571 0.0071 1.0000
16.500 0.9589 0.17055 0.16902 -0.0619 0.0068 1.0000
16.750 0.9444 0.18148 0.17996 -0.0670 0.0065 1.0000
17.000 0.9301 0.19357 0.19203 -0.0722 0.0067 1.0000
17.250 0.9246 0.20280 0.20124 -0.0764 0.0072 1.0000
19.500 0.6726 0.21202 0.21053 -0.0559 0.0083 1.0000
19.750 0.6741 0.21547 0.21398 -0.0572 0.0083 1.0000
20.000 0.6760 0.21890 0.21741 -0.0584 0.0083 1.0000
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Polar data table (+)
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