PW51 (pw51-pw) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: PW51 (pw51-pw) Reynolds number: 1,000,000 Max Cl/Cd: 90.75 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pw51-pw-1000000.txt Download as CSV file: xf-pw51-pw-1000000.csv |
XFOIL Version 6.96
Calculated polar for: PW51
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
------ -------- --------- --------- -------- -------- --------
-19.500 -0.8731 0.25751 0.25588 0.1039 1.0000 0.0043
-19.250 -0.8649 0.25452 0.25289 0.1021 1.0000 0.0044
-19.000 -0.8565 0.25144 0.24981 0.1001 1.0000 0.0044
-18.750 -0.8480 0.24832 0.24668 0.0981 1.0000 0.0045
-18.500 -0.8395 0.24515 0.24351 0.0960 1.0000 0.0046
-18.250 -0.8310 0.24190 0.24026 0.0940 1.0000 0.0047
-18.000 -0.8226 0.23857 0.23694 0.0920 1.0000 0.0049
-17.750 -0.8142 0.23519 0.23355 0.0900 1.0000 0.0050
-17.500 -0.8058 0.23174 0.23010 0.0880 1.0000 0.0052
-17.250 -0.7975 0.22817 0.22654 0.0859 1.0000 0.0055
-17.000 -0.7891 0.22445 0.22282 0.0839 1.0000 0.0059
-16.750 -0.7804 0.21966 0.21804 0.0809 1.0000 0.0063
-16.500 -0.7730 0.21558 0.21396 0.0784 1.0000 0.0063
-16.250 -0.7653 0.21178 0.21016 0.0763 1.0000 0.0064
-16.000 -0.7578 0.20796 0.20635 0.0742 1.0000 0.0064
-15.750 -0.7504 0.20411 0.20250 0.0722 1.0000 0.0064
-15.500 -0.7431 0.20023 0.19862 0.0702 1.0000 0.0064
-15.250 -0.7379 0.19614 0.19453 0.0691 1.0000 0.0066
-15.000 -0.7303 0.19309 0.19148 0.0678 1.0000 0.0067
-14.750 -0.7230 0.18987 0.18826 0.0662 1.0000 0.0068
-14.500 -0.7160 0.18654 0.18494 0.0647 1.0000 0.0070
-14.250 -0.7092 0.18304 0.18144 0.0630 1.0000 0.0071
-14.000 -0.7027 0.17939 0.17779 0.0613 1.0000 0.0073
-13.750 -0.6965 0.17562 0.17402 0.0596 1.0000 0.0074
-13.500 -0.6905 0.17177 0.17018 0.0579 1.0000 0.0076
-13.250 -0.6850 0.16786 0.16627 0.0562 1.0000 0.0078
-13.000 -0.6799 0.16386 0.16228 0.0545 1.0000 0.0080
-12.750 -0.6751 0.15974 0.15816 0.0528 1.0000 0.0083
-12.500 -0.6707 0.15524 0.15367 0.0509 1.0000 0.0086
-12.250 -0.6680 0.14983 0.14826 0.0480 1.0000 0.0090
-12.000 -0.6645 0.14526 0.14370 0.0460 1.0000 0.0090
-11.750 -0.6610 0.14078 0.13923 0.0441 1.0000 0.0091
-11.500 -0.6580 0.13618 0.13464 0.0423 1.0000 0.0091
-11.250 -0.6557 0.13152 0.12998 0.0404 1.0000 0.0091
-11.000 -0.6541 0.12671 0.12518 0.0384 1.0000 0.0091
-8.750 -0.8120 0.03292 0.03021 -0.0128 1.0000 0.0064
-8.500 -0.8114 0.02605 0.02262 -0.0120 1.0000 0.0065
-8.250 -0.7975 0.02223 0.01833 -0.0112 1.0000 0.0067
-8.000 -0.7775 0.01995 0.01577 -0.0106 1.0000 0.0068
-7.750 -0.7548 0.01838 0.01398 -0.0101 1.0000 0.0069
-7.500 -0.7308 0.01713 0.01258 -0.0097 1.0000 0.0071
-7.250 -0.7060 0.01605 0.01136 -0.0093 1.0000 0.0072
-7.000 -0.6808 0.01506 0.01025 -0.0090 1.0000 0.0074
-6.750 -0.6552 0.01416 0.00923 -0.0087 1.0000 0.0076
-6.500 -0.6292 0.01339 0.00838 -0.0084 1.0000 0.0078
-6.250 -0.6027 0.01277 0.00767 -0.0082 1.0000 0.0082
-6.000 -0.5760 0.01216 0.00700 -0.0080 1.0000 0.0086
-5.750 -0.5492 0.01160 0.00636 -0.0078 1.0000 0.0090
-5.500 -0.5236 0.01064 0.00530 -0.0074 1.0000 0.0096
-5.250 -0.4965 0.01008 0.00471 -0.0073 0.9990 0.0105
-4.750 -0.4327 0.00942 0.00397 -0.0088 0.9649 0.0125
-4.500 -0.4089 0.00896 0.00344 -0.0077 0.9438 0.0146
-4.250 -0.3849 0.00877 0.00319 -0.0066 0.9232 0.0168
-4.000 -0.3604 0.00848 0.00285 -0.0057 0.9022 0.0214
-3.750 -0.3348 0.00825 0.00257 -0.0050 0.8818 0.0276
-3.500 -0.3084 0.00805 0.00233 -0.0045 0.8604 0.0354
-3.250 -0.2818 0.00786 0.00211 -0.0041 0.8392 0.0477
-3.000 -0.2548 0.00766 0.00191 -0.0038 0.8168 0.0673
-2.750 -0.2278 0.00744 0.00173 -0.0036 0.7948 0.0969
-2.500 -0.2006 0.00719 0.00158 -0.0034 0.7726 0.1397
-2.250 -0.1734 0.00697 0.00143 -0.0033 0.7511 0.1869
-2.000 -0.1461 0.00670 0.00130 -0.0032 0.7301 0.2462
-1.500 -0.0921 0.00606 0.00109 -0.0031 0.6907 0.4154
-1.250 -0.0653 0.00570 0.00101 -0.0029 0.6713 0.5201
-1.000 -0.0389 0.00536 0.00095 -0.0027 0.6524 0.6252
-0.750 -0.0127 0.00510 0.00091 -0.0023 0.6339 0.7164
-0.500 0.0135 0.00491 0.00090 -0.0017 0.6159 0.7891
-0.250 0.0392 0.00480 0.00091 -0.0010 0.5972 0.8475
0.000 0.0647 0.00476 0.00093 -0.0002 0.5789 0.8915
0.500 0.1171 0.00483 0.00097 0.0012 0.5432 0.9496
0.750 0.1469 0.00491 0.00099 0.0010 0.5250 0.9670
1.000 0.1803 0.00501 0.00101 -0.0001 0.5063 0.9798
1.500 0.2534 0.00524 0.00106 -0.0037 0.4682 0.9936
1.750 0.2924 0.00536 0.00109 -0.0061 0.4477 0.9974
2.000 0.3276 0.00548 0.00112 -0.0078 0.4277 1.0000
2.250 0.3542 0.00558 0.00115 -0.0075 0.4090 1.0000
2.500 0.3809 0.00570 0.00119 -0.0073 0.3904 1.0000
2.750 0.4074 0.00583 0.00124 -0.0071 0.3731 1.0000
3.000 0.4340 0.00597 0.00131 -0.0068 0.3554 1.0000
3.250 0.4606 0.00610 0.00139 -0.0066 0.3389 1.0000
3.500 0.4872 0.00625 0.00147 -0.0063 0.3215 1.0000
3.750 0.5138 0.00640 0.00156 -0.0061 0.3057 1.0000
4.000 0.5404 0.00657 0.00167 -0.0058 0.2895 1.0000
4.250 0.5672 0.00674 0.00179 -0.0057 0.2732 1.0000
4.500 0.5940 0.00693 0.00192 -0.0055 0.2575 1.0000
5.000 0.6479 0.00733 0.00221 -0.0052 0.2253 1.0000
5.250 0.6749 0.00755 0.00237 -0.0051 0.2090 1.0000
5.500 0.7018 0.00779 0.00255 -0.0050 0.1911 1.0000
5.750 0.7286 0.00807 0.00276 -0.0050 0.1721 1.0000
6.000 0.7555 0.00835 0.00297 -0.0049 0.1554 1.0000
6.250 0.7823 0.00862 0.00320 -0.0048 0.1408 1.0000
6.500 0.8091 0.00892 0.00344 -0.0048 0.1265 1.0000
6.750 0.8358 0.00923 0.00371 -0.0047 0.1122 1.0000
7.000 0.8624 0.00957 0.00400 -0.0046 0.0982 1.0000
7.250 0.8888 0.00992 0.00431 -0.0046 0.0855 1.0000
7.500 0.9151 0.01031 0.00464 -0.0045 0.0726 1.0000
7.750 0.9411 0.01073 0.00502 -0.0044 0.0600 1.0000
8.000 0.9669 0.01119 0.00542 -0.0043 0.0480 1.0000
8.250 0.9925 0.01166 0.00585 -0.0042 0.0388 1.0000
8.500 1.0180 0.01216 0.00632 -0.0040 0.0317 1.0000
8.750 1.0435 0.01262 0.00678 -0.0039 0.0273 1.0000
9.000 1.0688 0.01311 0.00730 -0.0037 0.0236 1.0000
9.250 1.0943 0.01352 0.00774 -0.0036 0.0214 1.0000
9.500 1.1187 0.01416 0.00838 -0.0033 0.0182 1.0000
9.750 1.1438 0.01459 0.00887 -0.0032 0.0170 1.0000
10.000 1.1687 0.01504 0.00936 -0.0030 0.0154 1.0000
10.250 1.1921 0.01574 0.01009 -0.0027 0.0133 1.0000
10.500 1.2161 0.01630 0.01071 -0.0024 0.0122 1.0000
10.750 1.2401 0.01679 0.01126 -0.0022 0.0110 1.0000
11.000 1.2625 0.01754 0.01203 -0.0018 0.0095 1.0000
11.250 1.2848 0.01825 0.01281 -0.0015 0.0085 1.0000
11.500 1.3073 0.01888 0.01349 -0.0011 0.0075 1.0000
11.750 1.3253 0.02011 0.01481 -0.0004 0.0062 1.0000
12.000 1.3465 0.02082 0.01561 0.0000 0.0057 1.0000
12.250 1.3660 0.02171 0.01658 0.0006 0.0052 1.0000
12.500 1.3830 0.02282 0.01776 0.0013 0.0047 1.0000
12.750 1.3908 0.02486 0.01997 0.0026 0.0042 1.0000
13.000 1.4026 0.02625 0.02150 0.0035 0.0041 1.0000
13.250 1.4118 0.02762 0.02299 0.0047 0.0040 1.0000
13.500 1.4155 0.02932 0.02481 0.0060 0.0039 1.0000
13.750 1.4164 0.03153 0.02716 0.0065 0.0038 1.0000
14.000 1.4153 0.03434 0.03012 0.0061 0.0037 1.0000
14.250 1.4122 0.03783 0.03376 0.0047 0.0037 1.0000
14.500 1.4065 0.04209 0.03819 0.0024 0.0036 1.0000
14.750 1.3978 0.04710 0.04335 -0.0004 0.0036 1.0000
15.000 1.3852 0.05287 0.04927 -0.0037 0.0036 1.0000
15.250 1.3688 0.05935 0.05590 -0.0073 0.0036 1.0000
15.500 1.3492 0.06643 0.06313 -0.0111 0.0036 1.0000
15.750 1.3268 0.07398 0.07082 -0.0149 0.0036 1.0000
16.000 1.3027 0.08190 0.07887 -0.0188 0.0036 1.0000
16.250 1.2774 0.09013 0.08722 -0.0228 0.0037 1.0000
16.500 1.2525 0.09858 0.09578 -0.0269 0.0037 1.0000
16.750 1.2290 0.10697 0.10428 -0.0310 0.0037 1.0000
17.000 1.2068 0.11533 0.11275 -0.0351 0.0037 1.0000
17.250 1.1866 0.12346 0.12098 -0.0390 0.0038 1.0000
17.500 1.1676 0.13159 0.12920 -0.0431 0.0038 1.0000
17.750 1.1504 0.13947 0.13717 -0.0470 0.0038 1.0000
18.000 1.1353 0.14715 0.14494 -0.0510 0.0038 1.0000
18.250 1.1216 0.15477 0.15264 -0.0550 0.0038 1.0000
18.500 1.1084 0.16249 0.16044 -0.0592 0.0038 1.0000
18.750 1.0957 0.17037 0.16840 -0.0636 0.0038 1.0000
19.000 1.0836 0.17844 0.17655 -0.0681 0.0039 1.0000
19.250 1.0713 0.18697 0.18517 -0.0730 0.0039 1.0000
19.500 1.0565 0.19676 0.19506 -0.0787 0.0039 1.0000
|
Polar data table (+)
Polar graphs
<< Back to PW51 (pw51-pw)