NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9627 AIRFOIL (npl9627-il) Reynolds number: 50,000 Max Cl/Cd: 29.67 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9627-il-50000-n5.txt Download as CSV file: xf-npl9627-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9627 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7579 0.07132 0.06317 -0.0391 1.0000 0.0520
-10.500 -0.7797 0.06699 0.05865 -0.0390 1.0000 0.0519
-10.250 -0.7990 0.06299 0.05436 -0.0377 1.0000 0.0520
-10.000 -0.7935 0.06038 0.05175 -0.0368 1.0000 0.0531
-9.750 -0.7948 0.05727 0.04845 -0.0356 1.0000 0.0539
-9.500 -0.7953 0.05404 0.04494 -0.0341 1.0000 0.0547
-9.250 -0.7928 0.05079 0.04135 -0.0325 1.0000 0.0555
-9.000 -0.7866 0.04770 0.03789 -0.0309 1.0000 0.0563
-8.750 -0.7771 0.04481 0.03457 -0.0293 1.0000 0.0574
-8.500 -0.7646 0.04212 0.03141 -0.0277 1.0000 0.0587
-8.250 -0.7471 0.04008 0.02932 -0.0266 1.0000 0.0605
-8.000 -0.7297 0.03827 0.02738 -0.0254 1.0000 0.0633
-7.750 -0.7115 0.03639 0.02516 -0.0240 1.0000 0.0666
-7.500 -0.6932 0.03489 0.02372 -0.0228 1.0000 0.0702
-7.250 -0.6738 0.03340 0.02197 -0.0215 1.0000 0.0750
-7.000 -0.6559 0.03206 0.02074 -0.0202 1.0000 0.0799
-6.750 -0.6363 0.03075 0.01926 -0.0187 1.0000 0.0851
-6.500 -0.6186 0.02950 0.01807 -0.0172 1.0000 0.0907
-6.250 -0.6006 0.02832 0.01686 -0.0156 1.0000 0.0979
-5.750 -0.5655 0.02601 0.01460 -0.0123 1.0000 0.1204
-5.500 -0.5486 0.02475 0.01355 -0.0107 1.0000 0.1457
-5.250 -0.5322 0.02349 0.01268 -0.0092 1.0000 0.1974
-5.000 -0.5156 0.02262 0.01212 -0.0076 1.0000 0.2626
-4.750 -0.4984 0.02207 0.01175 -0.0059 1.0000 0.3168
-4.500 -0.4815 0.02166 0.01148 -0.0040 1.0000 0.3693
-4.250 -0.4665 0.02126 0.01133 -0.0018 1.0000 0.4287
-4.000 -0.4503 0.02087 0.01114 0.0004 1.0000 0.4766
-3.750 -0.4312 0.02049 0.01084 0.0022 1.0000 0.5107
-3.500 -0.4113 0.02015 0.01056 0.0037 1.0000 0.5418
-3.250 -0.3914 0.01985 0.01036 0.0054 1.0000 0.5744
-3.000 -0.3717 0.01960 0.01022 0.0071 1.0000 0.6107
-2.750 -0.3521 0.01942 0.01017 0.0089 1.0000 0.6514
-2.500 -0.3322 0.01932 0.01021 0.0108 1.0000 0.6959
-2.250 -0.3111 0.01934 0.01034 0.0125 1.0000 0.7452
-2.000 -0.2857 0.01947 0.01055 0.0135 0.9992 0.7974
-1.750 -0.2347 0.01977 0.01079 0.0097 0.9893 0.8507
-1.500 -0.1761 0.02011 0.01100 0.0042 0.9805 0.8952
-1.250 -0.1149 0.02036 0.01109 -0.0022 0.9706 0.9299
-1.000 -0.0477 0.02051 0.01109 -0.0100 0.9617 0.9562
-0.750 0.0227 0.02053 0.01097 -0.0187 0.9529 0.9773
-0.500 0.0912 0.02040 0.01075 -0.0272 0.9415 0.9947
-0.250 0.1413 0.02023 0.01051 -0.0321 0.9246 1.0000
0.000 0.1809 0.02007 0.01029 -0.0348 0.9046 1.0000
0.250 0.2182 0.01991 0.01007 -0.0368 0.8842 1.0000
0.500 0.2483 0.01981 0.00992 -0.0373 0.8608 1.0000
0.750 0.2773 0.01972 0.00979 -0.0374 0.8384 1.0000
1.000 0.3047 0.01967 0.00967 -0.0371 0.8168 1.0000
1.250 0.3307 0.01964 0.00958 -0.0364 0.7959 1.0000
1.500 0.3540 0.01967 0.00957 -0.0352 0.7740 1.0000
1.750 0.3765 0.01974 0.00959 -0.0339 0.7522 1.0000
2.000 0.3991 0.01983 0.00962 -0.0325 0.7311 1.0000
2.250 0.4216 0.01994 0.00969 -0.0312 0.7106 1.0000
2.500 0.4441 0.02008 0.00978 -0.0298 0.6908 1.0000
2.750 0.4664 0.02025 0.00990 -0.0284 0.6712 1.0000
3.250 0.5107 0.02068 0.01029 -0.0256 0.6314 1.0000
3.500 0.5326 0.02093 0.01054 -0.0242 0.6104 1.0000
3.750 0.5543 0.02117 0.01077 -0.0227 0.5884 1.0000
4.000 0.5757 0.02138 0.01092 -0.0210 0.5642 1.0000
4.250 0.5949 0.02159 0.01108 -0.0190 0.5343 1.0000
4.500 0.6132 0.02179 0.01115 -0.0168 0.5004 1.0000
4.750 0.6309 0.02204 0.01127 -0.0146 0.4640 1.0000
5.000 0.6491 0.02235 0.01150 -0.0127 0.4300 1.0000
5.250 0.6682 0.02275 0.01182 -0.0110 0.4002 1.0000
5.500 0.6868 0.02320 0.01220 -0.0093 0.3683 1.0000
5.750 0.7046 0.02375 0.01265 -0.0075 0.3339 1.0000
6.000 0.7217 0.02442 0.01319 -0.0058 0.2984 1.0000
6.250 0.7381 0.02525 0.01387 -0.0041 0.2626 1.0000
6.500 0.7539 0.02624 0.01468 -0.0024 0.2302 1.0000
6.750 0.7698 0.02731 0.01560 -0.0008 0.2046 1.0000
7.000 0.7864 0.02842 0.01658 0.0007 0.1868 1.0000
7.250 0.8042 0.02952 0.01763 0.0021 0.1731 1.0000
7.500 0.8227 0.03063 0.01875 0.0033 0.1621 1.0000
7.750 0.8411 0.03178 0.01982 0.0045 0.1538 1.0000
8.000 0.8612 0.03293 0.02108 0.0055 0.1461 1.0000
8.250 0.8807 0.03414 0.02223 0.0065 0.1399 1.0000
8.500 0.9006 0.03540 0.02369 0.0075 0.1332 1.0000
8.750 0.9203 0.03666 0.02489 0.0084 0.1278 1.0000
9.000 0.9389 0.03813 0.02659 0.0094 0.1222 1.0000
9.250 0.9570 0.03955 0.02812 0.0104 0.1172 1.0000
9.500 0.9762 0.04105 0.02958 0.0112 0.1129 1.0000
9.750 0.9906 0.04291 0.03178 0.0124 0.1086 1.0000
10.000 1.0059 0.04462 0.03365 0.0135 0.1048 1.0000
10.250 1.0253 0.04630 0.03526 0.0141 0.1016 1.0000
10.500 1.0313 0.04878 0.03817 0.0158 0.0988 1.0000
10.750 1.0367 0.05123 0.04094 0.0174 0.0961 1.0000
11.000 1.0430 0.05355 0.04347 0.0188 0.0936 1.0000
11.250 1.0518 0.05584 0.04588 0.0199 0.0917 1.0000
11.500 1.0595 0.05841 0.04853 0.0210 0.0901 1.0000
11.750 1.0420 0.06187 0.05237 0.0234 0.0892 1.0000
12.000 1.0203 0.06594 0.05676 0.0248 0.0886 1.0000
12.250 0.9935 0.07097 0.06208 0.0246 0.0882 1.0000
12.500 0.9601 0.07759 0.06896 0.0223 0.0882 1.0000
12.750 0.9171 0.08690 0.07848 0.0170 0.0886 1.0000
13.000 0.8630 0.10043 0.09214 0.0082 0.0893 1.0000
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Polar data table (+)
Polar graphs
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