NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Reynolds number: 50,000 Max Cl/Cd: 22.57 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nplx-il-50000-n5.txt Download as CSV file: xf-nplx-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL AIRFOIL FROM ARC CP 1372
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5768 0.09730 0.08929 -0.0327 1.0000 0.0510
-9.750 -0.5880 0.09070 0.08272 -0.0365 1.0000 0.0503
-9.500 -0.6058 0.08403 0.07606 -0.0405 1.0000 0.0496
-9.250 -0.6305 0.07772 0.06971 -0.0439 1.0000 0.0485
-9.000 -0.6621 0.07233 0.06426 -0.0454 1.0000 0.0473
-8.750 -0.6858 0.06832 0.06012 -0.0446 1.0000 0.0469
-8.500 -0.6975 0.06481 0.05645 -0.0436 1.0000 0.0470
-8.250 -0.7027 0.06169 0.05319 -0.0424 1.0000 0.0475
-8.000 -0.7049 0.05867 0.05000 -0.0410 1.0000 0.0482
-7.750 -0.7050 0.05560 0.04668 -0.0396 1.0000 0.0490
-7.500 -0.7025 0.05250 0.04330 -0.0381 1.0000 0.0499
-7.250 -0.6972 0.04940 0.03988 -0.0366 1.0000 0.0508
-7.000 -0.6891 0.04641 0.03651 -0.0350 1.0000 0.0520
-6.750 -0.6788 0.04353 0.03312 -0.0334 1.0000 0.0541
-6.500 -0.6649 0.04099 0.03032 -0.0321 1.0000 0.0563
-6.250 -0.6482 0.03903 0.02826 -0.0309 1.0000 0.0587
-6.000 -0.6302 0.03701 0.02597 -0.0296 1.0000 0.0614
-5.750 -0.6111 0.03511 0.02359 -0.0280 1.0000 0.0659
-5.500 -0.5910 0.03333 0.02186 -0.0269 1.0000 0.0694
-5.250 -0.5701 0.03192 0.02035 -0.0255 1.0000 0.0745
-5.000 -0.5483 0.03056 0.01884 -0.0239 1.0000 0.0802
-4.750 -0.5280 0.02939 0.01771 -0.0223 1.0000 0.0861
-4.500 -0.5078 0.02843 0.01660 -0.0204 1.0000 0.0936
-4.250 -0.4908 0.02737 0.01565 -0.0185 1.0000 0.1004
-4.000 -0.4741 0.02644 0.01467 -0.0166 1.0000 0.1099
-3.750 -0.4581 0.02547 0.01370 -0.0149 1.0000 0.1202
-3.500 -0.4418 0.02446 0.01275 -0.0135 1.0000 0.1348
-3.250 -0.4247 0.02333 0.01173 -0.0124 1.0000 0.1560
-3.000 -0.4068 0.02169 0.01043 -0.0121 1.0000 0.2050
-2.750 -0.4002 0.02020 0.01087 -0.0085 1.0000 0.5391
-2.500 -0.3857 0.02069 0.01133 -0.0048 1.0000 0.6076
-2.250 -0.3717 0.02116 0.01176 -0.0010 1.0000 0.6482
-2.000 -0.3584 0.02158 0.01216 0.0031 1.0000 0.6791
-1.750 -0.3456 0.02191 0.01249 0.0071 1.0000 0.7064
-1.500 -0.3340 0.02220 0.01275 0.0115 1.0000 0.7343
-1.250 -0.3218 0.02234 0.01287 0.0155 1.0000 0.7558
-1.000 -0.3038 0.02224 0.01267 0.0173 1.0000 0.7688
-0.750 -0.2819 0.02204 0.01234 0.0178 1.0000 0.7761
-0.500 -0.2590 0.02184 0.01202 0.0179 1.0000 0.7816
-0.250 -0.2369 0.02168 0.01178 0.0183 1.0000 0.7872
0.000 -0.2133 0.02154 0.01155 0.0182 1.0000 0.7937
0.250 -0.1912 0.02144 0.01139 0.0186 1.0000 0.7994
0.500 -0.1688 0.02137 0.01129 0.0189 1.0000 0.8064
0.750 -0.1465 0.02133 0.01122 0.0191 1.0000 0.8137
1.000 -0.1142 0.02148 0.01136 0.0174 0.9947 0.8209
1.250 -0.0789 0.02166 0.01154 0.0151 0.9875 0.8283
1.500 -0.0426 0.02185 0.01178 0.0128 0.9789 0.8364
1.750 -0.0024 0.02206 0.01204 0.0098 0.9677 0.8451
2.000 0.0387 0.02223 0.01229 0.0068 0.9553 0.8543
2.250 0.0807 0.02233 0.01251 0.0038 0.9417 0.8638
2.500 0.1226 0.02238 0.01270 0.0009 0.9277 0.8745
2.750 0.1650 0.02238 0.01288 -0.0018 0.9138 0.8860
3.000 0.2062 0.02236 0.01306 -0.0043 0.9003 0.8985
3.250 0.2499 0.02225 0.01320 -0.0071 0.8847 0.9127
3.500 0.3095 0.02139 0.01262 -0.0109 0.8493 0.9223
3.750 0.3687 0.01981 0.01122 -0.0124 0.7782 0.9304
4.000 0.4099 0.01904 0.01051 -0.0124 0.6738 0.9449
4.250 0.4495 0.01992 0.00965 -0.0118 0.3566 0.9563
4.500 0.4725 0.02195 0.01044 -0.0126 0.1810 0.9903
4.750 0.4907 0.02309 0.01122 -0.0119 0.1461 1.0000
5.000 0.5119 0.02413 0.01207 -0.0115 0.1293 1.0000
5.250 0.5359 0.02512 0.01299 -0.0114 0.1165 1.0000
5.500 0.5623 0.02619 0.01401 -0.0115 0.1077 1.0000
5.750 0.5914 0.02730 0.01517 -0.0119 0.1016 1.0000
6.000 0.6221 0.02868 0.01640 -0.0125 0.0967 1.0000
6.250 0.6523 0.02986 0.01777 -0.0128 0.0911 1.0000
6.500 0.6809 0.03119 0.01915 -0.0131 0.0864 1.0000
6.750 0.7101 0.03289 0.02081 -0.0136 0.0837 1.0000
7.000 0.7383 0.03477 0.02285 -0.0137 0.0818 1.0000
7.250 0.7637 0.03665 0.02509 -0.0134 0.0800 1.0000
7.500 0.7865 0.03860 0.02737 -0.0128 0.0775 1.0000
7.750 0.8075 0.04053 0.02956 -0.0121 0.0747 1.0000
8.000 0.8277 0.04258 0.03180 -0.0115 0.0726 1.0000
8.250 0.8461 0.04500 0.03448 -0.0107 0.0715 1.0000
8.500 0.8626 0.04766 0.03739 -0.0097 0.0707 1.0000
8.750 0.8768 0.05062 0.04061 -0.0087 0.0700 1.0000
9.000 0.8880 0.05390 0.04413 -0.0076 0.0695 1.0000
9.250 0.8918 0.05716 0.04786 -0.0057 0.0689 1.0000
9.500 0.8904 0.06067 0.05183 -0.0038 0.0682 1.0000
9.750 0.8848 0.06439 0.05594 -0.0020 0.0675 1.0000
10.000 0.8745 0.06833 0.06019 -0.0004 0.0671 1.0000
10.250 0.8591 0.07239 0.06449 0.0010 0.0669 1.0000
10.500 0.8389 0.07654 0.06880 0.0021 0.0670 1.0000
10.750 0.8175 0.08138 0.07376 0.0016 0.0672 1.0000
11.000 0.7957 0.08714 0.07960 -0.0008 0.0676 1.0000
11.250 0.7769 0.09374 0.08625 -0.0047 0.0680 1.0000
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Polar data table (+)
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