NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NPL 9627 AIRFOIL (npl9627-il) Reynolds number: 100,000 Max Cl/Cd: 42.32 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9627-il-100000.txt Download as CSV file: xf-npl9627-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6996 0.07782 0.07254 -0.0353 1.0000 0.0839
-10.000 -0.5156 0.08564 0.08070 -0.0240 1.0000 0.1019
-9.750 -0.8017 0.05979 0.05364 -0.0361 1.0000 0.0671
-9.500 -0.8040 0.05569 0.04926 -0.0346 1.0000 0.0656
-9.250 -0.8044 0.05171 0.04501 -0.0329 1.0000 0.0652
-9.000 -0.8042 0.04792 0.04085 -0.0308 1.0000 0.0649
-8.750 -0.8011 0.04440 0.03689 -0.0285 1.0000 0.0649
-8.500 -0.7940 0.04122 0.03326 -0.0261 1.0000 0.0652
-8.250 -0.7852 0.03854 0.03005 -0.0236 1.0000 0.0660
-8.000 -0.7699 0.03584 0.02719 -0.0221 1.0000 0.0679
-7.750 -0.7513 0.03392 0.02521 -0.0208 1.0000 0.0703
-7.500 -0.7345 0.03205 0.02302 -0.0190 1.0000 0.0728
-7.250 -0.7165 0.03023 0.02079 -0.0170 1.0000 0.0746
-7.000 -0.6946 0.02804 0.01853 -0.0159 1.0000 0.0764
-6.750 -0.6725 0.02644 0.01692 -0.0147 1.0000 0.0792
-6.500 -0.6506 0.02506 0.01542 -0.0134 1.0000 0.0828
-6.250 -0.6292 0.02361 0.01402 -0.0121 1.0000 0.0869
-6.000 -0.6091 0.02260 0.01303 -0.0106 1.0000 0.0932
-5.750 -0.5903 0.02154 0.01209 -0.0091 1.0000 0.1012
-5.500 -0.5719 0.02060 0.01123 -0.0074 1.0000 0.1114
-5.250 -0.5539 0.01964 0.01037 -0.0056 1.0000 0.1231
-5.000 -0.5366 0.01862 0.00953 -0.0037 1.0000 0.1445
-4.750 -0.5240 0.01683 0.00860 -0.0014 1.0000 0.2475
-4.500 -0.5079 0.01627 0.00843 0.0005 1.0000 0.3481
-4.250 -0.4889 0.01606 0.00829 0.0021 1.0000 0.3954
-4.000 -0.4689 0.01582 0.00811 0.0035 1.0000 0.4318
-3.750 -0.4488 0.01557 0.00797 0.0048 1.0000 0.4676
-3.500 -0.4291 0.01532 0.00790 0.0062 1.0000 0.5093
-3.250 -0.4095 0.01509 0.00791 0.0078 1.0000 0.5552
-3.000 -0.3897 0.01490 0.00796 0.0093 1.0000 0.6027
-2.750 -0.3697 0.01475 0.00803 0.0108 1.0000 0.6510
-2.500 -0.3501 0.01466 0.00818 0.0126 1.0000 0.7002
-2.250 -0.3313 0.01467 0.00840 0.0146 1.0000 0.7559
-2.000 -0.3136 0.01486 0.00878 0.0171 1.0000 0.8173
-1.750 -0.2733 0.01534 0.00932 0.0157 0.9938 0.8841
-1.500 -0.2101 0.01596 0.00983 0.0098 0.9863 0.9348
-1.250 -0.1278 0.01653 0.01023 -0.0004 0.9828 0.9647
-1.000 -0.0360 0.01680 0.01034 -0.0128 0.9805 0.9832
-0.750 0.0525 0.01672 0.01016 -0.0250 0.9745 0.9983
-0.500 0.1195 0.01642 0.00979 -0.0334 0.9617 1.0000
-0.250 0.1787 0.01606 0.00937 -0.0399 0.9461 1.0000
0.000 0.2282 0.01569 0.00897 -0.0444 0.9269 1.0000
0.250 0.2688 0.01534 0.00857 -0.0467 0.9054 1.0000
0.500 0.2999 0.01505 0.00823 -0.0469 0.8824 1.0000
0.750 0.3230 0.01488 0.00802 -0.0457 0.8570 1.0000
1.000 0.3457 0.01474 0.00780 -0.0442 0.8343 1.0000
1.250 0.3678 0.01465 0.00763 -0.0426 0.8131 1.0000
1.500 0.3889 0.01466 0.00759 -0.0410 0.7902 1.0000
1.750 0.4103 0.01470 0.00755 -0.0394 0.7686 1.0000
2.000 0.4319 0.01473 0.00752 -0.0378 0.7470 1.0000
2.250 0.4536 0.01478 0.00746 -0.0361 0.7254 1.0000
2.500 0.4749 0.01486 0.00745 -0.0344 0.7017 1.0000
2.750 0.4960 0.01493 0.00744 -0.0327 0.6767 1.0000
3.000 0.5176 0.01501 0.00739 -0.0309 0.6524 1.0000
3.250 0.5386 0.01513 0.00744 -0.0293 0.6261 1.0000
3.500 0.5599 0.01524 0.00742 -0.0275 0.6003 1.0000
3.750 0.5808 0.01537 0.00750 -0.0259 0.5731 1.0000
4.000 0.6022 0.01554 0.00758 -0.0244 0.5481 1.0000
4.250 0.6237 0.01575 0.00772 -0.0229 0.5243 1.0000
4.500 0.6448 0.01596 0.00790 -0.0214 0.4979 1.0000
4.750 0.6655 0.01618 0.00805 -0.0199 0.4707 1.0000
5.000 0.6856 0.01641 0.00820 -0.0182 0.4403 1.0000
5.250 0.7049 0.01670 0.00840 -0.0164 0.4055 1.0000
5.500 0.7229 0.01708 0.00867 -0.0145 0.3611 1.0000
5.750 0.7373 0.01781 0.00903 -0.0121 0.3018 1.0000
6.000 0.7500 0.01898 0.00976 -0.0096 0.2396 1.0000
6.250 0.7662 0.02010 0.01057 -0.0076 0.2075 1.0000
6.500 0.7851 0.02107 0.01139 -0.0061 0.1902 1.0000
6.750 0.8056 0.02202 0.01224 -0.0048 0.1780 1.0000
7.000 0.8267 0.02303 0.01311 -0.0037 0.1685 1.0000
7.250 0.8485 0.02391 0.01401 -0.0027 0.1597 1.0000
7.500 0.8707 0.02500 0.01506 -0.0019 0.1521 1.0000
7.750 0.8928 0.02595 0.01602 -0.0010 0.1448 1.0000
8.000 0.9159 0.02727 0.01730 -0.0004 0.1387 1.0000
8.250 0.9375 0.02835 0.01853 0.0006 0.1327 1.0000
8.500 0.9620 0.02991 0.01991 0.0008 0.1272 1.0000
8.750 0.9817 0.03123 0.02155 0.0021 0.1226 1.0000
9.000 1.0027 0.03270 0.02318 0.0031 0.1183 1.0000
9.250 1.0262 0.03458 0.02496 0.0033 0.1144 1.0000
9.500 1.0416 0.03652 0.02730 0.0049 0.1112 1.0000
9.750 1.0566 0.03842 0.02953 0.0065 0.1080 1.0000
10.000 1.0733 0.04047 0.03177 0.0077 0.1055 1.0000
10.250 1.0911 0.04267 0.03407 0.0085 0.1033 1.0000
10.500 1.1051 0.04594 0.03747 0.0094 0.1013 1.0000
10.750 1.1051 0.04864 0.04070 0.0122 0.1001 1.0000
11.000 1.1016 0.05184 0.04436 0.0148 0.0991 1.0000
11.250 1.0937 0.05546 0.04838 0.0173 0.0986 1.0000
11.500 1.0795 0.05938 0.05265 0.0199 0.0985 1.0000
11.750 1.0578 0.06338 0.05693 0.0226 0.0986 1.0000
12.000 1.0304 0.06783 0.06160 0.0244 0.0991 1.0000
12.250 1.0003 0.07326 0.06722 0.0243 0.0997 1.0000
12.500 0.9710 0.07975 0.07386 0.0223 0.1005 1.0000
12.750 0.9480 0.08684 0.08104 0.0196 0.1012 1.0000
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Polar data table (+)
Polar graphs
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