PW51 (pw51-pw) Xfoil prediction polar at RE=2,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: PW51 (pw51-pw) Reynolds number: 2,000,000 Max Cl/Cd: 104.22 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pw51-pw-2000000.txt Download as CSV file: xf-pw51-pw-2000000.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 = 2.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-20.000 -0.5955 0.22138 0.22036 0.0614 1.0000 0.0028
-19.750 -0.5912 0.21873 0.21770 0.0602 1.0000 0.0028
-19.500 -0.5868 0.21608 0.21505 0.0590 1.0000 0.0029
-19.250 -0.5825 0.21340 0.21237 0.0578 1.0000 0.0030
-19.000 -0.5782 0.21072 0.20969 0.0566 1.0000 0.0031
-18.750 -0.5740 0.20801 0.20698 0.0554 1.0000 0.0033
-18.500 -0.5698 0.20527 0.20424 0.0543 1.0000 0.0035
-18.250 -0.5656 0.20243 0.20139 0.0531 1.0000 0.0038
-18.000 -0.5615 0.19922 0.19818 0.0518 1.0000 0.0041
-17.750 -0.5581 0.19610 0.19506 0.0505 1.0000 0.0041
-17.500 -0.5547 0.19308 0.19205 0.0493 1.0000 0.0042
-17.250 -0.5513 0.19011 0.18907 0.0481 1.0000 0.0042
-17.000 -0.5478 0.18727 0.18623 0.0469 1.0000 0.0042
-16.750 -0.5443 0.18447 0.18342 0.0457 1.0000 0.0042
-16.500 -0.5409 0.18169 0.18065 0.0446 1.0000 0.0042
-11.750 -1.0709 0.04047 0.03884 -0.0129 1.0000 0.0033
-11.500 -1.0774 0.03534 0.03340 -0.0132 1.0000 0.0033
-11.250 -1.0718 0.03187 0.02968 -0.0128 1.0000 0.0034
-11.000 -1.0596 0.02936 0.02695 -0.0124 1.0000 0.0035
-10.750 -1.0441 0.02728 0.02469 -0.0119 1.0000 0.0036
-10.500 -1.0261 0.02554 0.02277 -0.0114 1.0000 0.0037
-10.250 -1.0063 0.02407 0.02116 -0.0109 1.0000 0.0038
-10.000 -0.9852 0.02278 0.01972 -0.0105 1.0000 0.0039
-9.750 -0.9627 0.02171 0.01853 -0.0102 1.0000 0.0040
-9.500 -0.9395 0.02075 0.01746 -0.0098 1.0000 0.0041
-9.250 -0.9153 0.01996 0.01657 -0.0096 1.0000 0.0041
-9.000 -0.8904 0.01933 0.01586 -0.0093 1.0000 0.0042
-8.750 -0.8697 0.01742 0.01370 -0.0087 1.0000 0.0043
-8.500 -0.8497 0.01523 0.01120 -0.0080 1.0000 0.0044
-8.250 -0.8259 0.01401 0.00983 -0.0075 1.0000 0.0045
-8.000 -0.8007 0.01315 0.00887 -0.0072 1.0000 0.0046
-7.750 -0.7748 0.01247 0.00810 -0.0069 1.0000 0.0048
-7.500 -0.7485 0.01188 0.00744 -0.0067 1.0000 0.0049
-7.250 -0.7218 0.01135 0.00686 -0.0066 1.0000 0.0050
-7.000 -0.6949 0.01085 0.00631 -0.0064 1.0000 0.0051
-6.750 -0.6678 0.01039 0.00580 -0.0063 1.0000 0.0053
-6.500 -0.6406 0.00995 0.00532 -0.0062 1.0000 0.0054
-6.250 -0.6094 0.00954 0.00485 -0.0069 0.9845 0.0057
-6.000 -0.5828 0.00922 0.00448 -0.0065 0.9649 0.0059
-5.750 -0.5592 0.00900 0.00418 -0.0054 0.9443 0.0062
-5.500 -0.5343 0.00885 0.00398 -0.0046 0.9246 0.0064
-5.250 -0.5093 0.00836 0.00337 -0.0038 0.9042 0.0075
-5.000 -0.4828 0.00818 0.00311 -0.0034 0.8840 0.0082
-4.750 -0.4557 0.00802 0.00287 -0.0031 0.8632 0.0088
-4.500 -0.4285 0.00780 0.00256 -0.0028 0.8418 0.0100
-4.250 -0.4009 0.00763 0.00233 -0.0026 0.8207 0.0120
-4.000 -0.3732 0.00746 0.00210 -0.0025 0.7985 0.0152
-3.750 -0.3453 0.00733 0.00192 -0.0024 0.7768 0.0194
-3.500 -0.3173 0.00721 0.00176 -0.0023 0.7548 0.0237
-3.250 -0.2893 0.00708 0.00160 -0.0023 0.7337 0.0311
-3.000 -0.2612 0.00696 0.00146 -0.0022 0.7128 0.0413
-2.750 -0.2331 0.00682 0.00133 -0.0022 0.6929 0.0573
-2.500 -0.2050 0.00668 0.00121 -0.0023 0.6741 0.0778
-2.250 -0.1769 0.00651 0.00110 -0.0023 0.6555 0.1079
-2.000 -0.1489 0.00633 0.00099 -0.0023 0.6372 0.1465
-1.750 -0.1208 0.00618 0.00090 -0.0024 0.6196 0.1847
-1.500 -0.0928 0.00600 0.00083 -0.0024 0.6021 0.2345
-1.250 -0.0650 0.00577 0.00076 -0.0025 0.5850 0.2983
-1.000 -0.0372 0.00556 0.00069 -0.0025 0.5674 0.3677
-0.750 -0.0095 0.00533 0.00065 -0.0026 0.5498 0.4471
-0.500 0.0181 0.00509 0.00061 -0.0026 0.5320 0.5343
-0.250 0.0457 0.00490 0.00059 -0.0026 0.5152 0.6100
0.000 0.0733 0.00471 0.00058 -0.0025 0.4990 0.6864
0.250 0.1007 0.00456 0.00058 -0.0024 0.4825 0.7529
0.500 0.1279 0.00446 0.00059 -0.0021 0.4670 0.8092
0.750 0.1549 0.00439 0.00062 -0.0018 0.4507 0.8563
1.000 0.1818 0.00438 0.00065 -0.0014 0.4344 0.8906
1.250 0.2084 0.00440 0.00069 -0.0009 0.4174 0.9187
1.500 0.2344 0.00445 0.00074 -0.0003 0.4005 0.9446
1.750 0.2612 0.00453 0.00078 0.0001 0.3834 0.9626
2.000 0.2906 0.00462 0.00082 -0.0001 0.3658 0.9770
2.250 0.3224 0.00473 0.00087 -0.0009 0.3494 0.9862
2.500 0.3563 0.00486 0.00092 -0.0022 0.3315 0.9927
2.750 0.3914 0.00500 0.00098 -0.0038 0.3145 0.9957
3.000 0.4266 0.00514 0.00105 -0.0055 0.2970 0.9980
3.250 0.4615 0.00527 0.00112 -0.0070 0.2818 1.0000
3.500 0.4879 0.00539 0.00119 -0.0067 0.2674 1.0000
3.750 0.5144 0.00553 0.00127 -0.0065 0.2528 1.0000
4.000 0.5410 0.00567 0.00136 -0.0062 0.2393 1.0000
4.250 0.5676 0.00583 0.00146 -0.0060 0.2244 1.0000
4.500 0.5943 0.00599 0.00156 -0.0057 0.2103 1.0000
4.750 0.6212 0.00617 0.00169 -0.0056 0.1950 1.0000
5.000 0.6481 0.00636 0.00182 -0.0054 0.1792 1.0000
5.250 0.6751 0.00660 0.00197 -0.0053 0.1608 1.0000
5.500 0.7021 0.00683 0.00213 -0.0053 0.1450 1.0000
5.750 0.7293 0.00705 0.00230 -0.0052 0.1320 1.0000
6.000 0.7565 0.00728 0.00247 -0.0052 0.1192 1.0000
6.250 0.7837 0.00752 0.00266 -0.0051 0.1070 1.0000
6.500 0.8107 0.00780 0.00288 -0.0051 0.0937 1.0000
6.750 0.8377 0.00808 0.00311 -0.0051 0.0812 1.0000
7.000 0.8644 0.00843 0.00338 -0.0050 0.0660 1.0000
7.250 0.8911 0.00877 0.00365 -0.0050 0.0541 1.0000
7.500 0.9178 0.00910 0.00393 -0.0050 0.0450 1.0000
7.750 0.9445 0.00942 0.00423 -0.0049 0.0376 1.0000
8.000 0.9711 0.00976 0.00454 -0.0049 0.0311 1.0000
8.250 0.9974 0.01015 0.00488 -0.0048 0.0253 1.0000
8.500 1.0240 0.01045 0.00519 -0.0048 0.0225 1.0000
8.750 1.0502 0.01083 0.00556 -0.0047 0.0190 1.0000
9.000 1.0766 0.01115 0.00589 -0.0046 0.0172 1.0000
9.250 1.1028 0.01148 0.00624 -0.0046 0.0157 1.0000
9.500 1.1285 0.01190 0.00665 -0.0044 0.0135 1.0000
9.750 1.1545 0.01225 0.00702 -0.0044 0.0124 1.0000
10.000 1.1803 0.01261 0.00740 -0.0043 0.0113 1.0000
10.250 1.2053 0.01308 0.00788 -0.0041 0.0096 1.0000
10.500 1.2307 0.01349 0.00831 -0.0040 0.0086 1.0000
10.750 1.2555 0.01394 0.00878 -0.0038 0.0076 1.0000
11.000 1.2796 0.01450 0.00936 -0.0036 0.0062 1.0000
11.250 1.3041 0.01497 0.00985 -0.0034 0.0055 1.0000
11.500 1.3269 0.01569 0.01059 -0.0031 0.0041 1.0000
11.750 1.3504 0.01623 0.01119 -0.0028 0.0036 1.0000
12.000 1.3722 0.01701 0.01201 -0.0024 0.0029 1.0000
12.250 1.3928 0.01793 0.01303 -0.0018 0.0025 1.0000
12.500 1.4146 0.01860 0.01376 -0.0014 0.0024 1.0000
12.750 1.4356 0.01934 0.01457 -0.0010 0.0023 1.0000
13.000 1.4556 0.02015 0.01545 -0.0004 0.0023 1.0000
13.250 1.4745 0.02102 0.01640 0.0002 0.0022 1.0000
13.500 1.4922 0.02197 0.01744 0.0009 0.0022 1.0000
13.750 1.5086 0.02298 0.01854 0.0016 0.0021 1.0000
14.000 1.5234 0.02404 0.01969 0.0025 0.0020 1.0000
14.250 1.5364 0.02519 0.02092 0.0034 0.0020 1.0000
14.500 1.5434 0.02646 0.02228 0.0050 0.0019 1.0000
14.750 1.5472 0.02806 0.02398 0.0062 0.0019 1.0000
15.000 1.5495 0.03007 0.02610 0.0068 0.0019 1.0000
15.250 1.5494 0.03265 0.02879 0.0065 0.0019 1.0000
15.500 1.5476 0.03579 0.03206 0.0055 0.0018 1.0000
15.750 1.5434 0.03958 0.03598 0.0038 0.0018 1.0000
16.000 1.5358 0.04413 0.04065 0.0014 0.0018 1.0000
16.250 1.5237 0.04953 0.04619 -0.0015 0.0018 1.0000
16.500 1.5061 0.05594 0.05275 -0.0049 0.0018 1.0000
16.750 1.4846 0.06304 0.05999 -0.0087 0.0018 1.0000
17.000 1.4585 0.07094 0.06803 -0.0127 0.0018 1.0000
17.250 1.4270 0.07988 0.07712 -0.0171 0.0018 1.0000
17.500 1.3913 0.08972 0.08710 -0.0219 0.0019 1.0000
17.750 1.3545 0.10009 0.09761 -0.0270 0.0019 1.0000
18.000 1.3175 0.11087 0.10853 -0.0323 0.0019 1.0000
18.250 1.2807 0.12183 0.11962 -0.0377 0.0019 1.0000
18.500 1.2463 0.13283 0.13074 -0.0434 0.0020 1.0000
18.750 1.2164 0.14315 0.14117 -0.0487 0.0020 1.0000
19.000 1.1886 0.15357 0.15170 -0.0543 0.0020 1.0000
19.250 1.1659 0.16321 0.16143 -0.0597 0.0021 1.0000
19.500 1.1475 0.17216 0.17046 -0.0648 0.0021 1.0000
19.750 1.1345 0.18016 0.17853 -0.0695 0.0021 1.0000
20.000 1.1218 0.18842 0.18686 -0.0744 0.0021 1.0000
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