NPL 9626 AIRFOIL (npl9626-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NPL 9626 AIRFOIL (npl9626-il) Reynolds number: 100,000 Max Cl/Cd: 42.14 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9626-il-100000.txt Download as CSV file: xf-npl9626-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9626 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5917 0.10104 0.09590 -0.0054 1.0000 0.1688
-9.500 -0.6808 0.05527 0.04991 -0.0384 1.0000 0.0783
-9.250 -0.8014 0.05760 0.05115 -0.0302 1.0000 0.0712
-9.000 -0.7947 0.05351 0.04685 -0.0288 1.0000 0.0685
-8.750 -0.7924 0.04948 0.04253 -0.0269 1.0000 0.0675
-8.500 -0.7890 0.04584 0.03850 -0.0246 1.0000 0.0673
-8.250 -0.7831 0.04288 0.03506 -0.0221 1.0000 0.0686
-8.000 -0.7762 0.04086 0.03240 -0.0191 1.0000 0.0702
-7.750 -0.7614 0.03723 0.02870 -0.0180 1.0000 0.0721
-7.500 -0.7441 0.03486 0.02615 -0.0165 1.0000 0.0736
-7.250 -0.7264 0.03292 0.02401 -0.0148 1.0000 0.0761
-7.000 -0.7084 0.03103 0.02178 -0.0130 1.0000 0.0786
-6.750 -0.6887 0.02922 0.01960 -0.0112 1.0000 0.0805
-6.500 -0.6664 0.02702 0.01729 -0.0101 1.0000 0.0832
-6.250 -0.6441 0.02548 0.01576 -0.0090 1.0000 0.0872
-6.000 -0.6223 0.02435 0.01448 -0.0076 1.0000 0.0925
-5.750 -0.6013 0.02294 0.01321 -0.0065 1.0000 0.0998
-5.500 -0.5807 0.02191 0.01214 -0.0051 1.0000 0.1085
-5.250 -0.5608 0.02075 0.01114 -0.0037 1.0000 0.1166
-5.000 -0.5425 0.01965 0.01015 -0.0019 1.0000 0.1273
-4.750 -0.5254 0.01858 0.00923 0.0000 1.0000 0.1440
-4.500 -0.5099 0.01726 0.00830 0.0021 1.0000 0.1849
-4.250 -0.5008 0.01540 0.00774 0.0049 1.0000 0.3903
-4.000 -0.4844 0.01488 0.00761 0.0072 1.0000 0.4816
-3.750 -0.4658 0.01458 0.00753 0.0091 1.0000 0.5424
-3.500 -0.4469 0.01438 0.00752 0.0111 1.0000 0.5991
-3.250 -0.4280 0.01425 0.00761 0.0133 1.0000 0.6531
-3.000 -0.4089 0.01421 0.00774 0.0155 1.0000 0.7039
-2.750 -0.3904 0.01425 0.00793 0.0180 1.0000 0.7534
-2.500 -0.3735 0.01444 0.00826 0.0212 1.0000 0.8029
-2.250 -0.3556 0.01477 0.00868 0.0244 1.0000 0.8484
-2.000 -0.3334 0.01515 0.00905 0.0264 1.0000 0.8906
-1.750 -0.2962 0.01561 0.00944 0.0251 1.0000 0.9245
-1.500 -0.2380 0.01615 0.00984 0.0194 1.0000 0.9489
-1.250 -0.1681 0.01659 0.01013 0.0109 0.9994 0.9687
-1.000 -0.0834 0.01683 0.01024 -0.0006 0.9944 0.9818
-0.750 -0.0001 0.01680 0.01012 -0.0120 0.9871 0.9922
-0.500 0.0801 0.01658 0.00985 -0.0230 0.9777 1.0000
-0.250 0.1459 0.01620 0.00944 -0.0313 0.9618 1.0000
0.000 0.2053 0.01575 0.00898 -0.0379 0.9425 1.0000
0.250 0.2498 0.01533 0.00856 -0.0413 0.9152 1.0000
0.500 0.2833 0.01498 0.00816 -0.0422 0.8854 1.0000
0.750 0.3079 0.01472 0.00783 -0.0411 0.8552 1.0000
1.000 0.3287 0.01457 0.00759 -0.0394 0.8249 1.0000
1.250 0.3492 0.01452 0.00745 -0.0377 0.7961 1.0000
1.500 0.3707 0.01450 0.00731 -0.0361 0.7714 1.0000
1.750 0.3924 0.01458 0.00732 -0.0349 0.7462 1.0000
2.000 0.4146 0.01469 0.00734 -0.0337 0.7245 1.0000
2.250 0.4371 0.01485 0.00741 -0.0326 0.7051 1.0000
2.500 0.4598 0.01504 0.00753 -0.0316 0.6870 1.0000
2.750 0.4825 0.01524 0.00769 -0.0305 0.6696 1.0000
3.000 0.5050 0.01545 0.00785 -0.0294 0.6520 1.0000
3.250 0.5270 0.01563 0.00797 -0.0281 0.6333 1.0000
3.500 0.5478 0.01576 0.00807 -0.0265 0.6099 1.0000
3.750 0.5681 0.01579 0.00796 -0.0245 0.5838 1.0000
4.000 0.5878 0.01585 0.00796 -0.0226 0.5557 1.0000
4.250 0.6090 0.01598 0.00802 -0.0210 0.5334 1.0000
4.500 0.6306 0.01616 0.00816 -0.0196 0.5137 1.0000
4.750 0.6512 0.01631 0.00837 -0.0181 0.4901 1.0000
5.000 0.6713 0.01644 0.00846 -0.0163 0.4638 1.0000
5.250 0.6902 0.01656 0.00858 -0.0144 0.4298 1.0000
5.500 0.7054 0.01674 0.00866 -0.0117 0.3627 1.0000
5.750 0.7078 0.01856 0.00929 -0.0077 0.1842 1.0000
6.000 0.7200 0.02001 0.01039 -0.0052 0.1510 1.0000
6.250 0.7354 0.02113 0.01137 -0.0031 0.1363 1.0000
6.500 0.7519 0.02225 0.01238 -0.0012 0.1262 1.0000
6.750 0.7705 0.02333 0.01336 0.0003 0.1179 1.0000
7.000 0.7912 0.02453 0.01453 0.0016 0.1114 1.0000
7.250 0.8131 0.02571 0.01566 0.0026 0.1056 1.0000
7.500 0.8366 0.02732 0.01719 0.0033 0.1005 1.0000
7.750 0.8598 0.02863 0.01866 0.0042 0.0964 1.0000
8.000 0.8835 0.03019 0.02029 0.0049 0.0930 1.0000
8.250 0.9085 0.03242 0.02244 0.0051 0.0898 1.0000
8.500 0.9280 0.03426 0.02459 0.0064 0.0872 1.0000
8.750 0.9463 0.03615 0.02682 0.0079 0.0850 1.0000
9.000 0.9633 0.03840 0.02941 0.0094 0.0835 1.0000
9.250 0.9791 0.04062 0.03189 0.0108 0.0816 1.0000
9.500 0.9986 0.04279 0.03405 0.0114 0.0789 1.0000
9.750 1.0118 0.04689 0.03826 0.0122 0.0771 1.0000
10.000 1.0158 0.04926 0.04114 0.0148 0.0764 1.0000
10.250 1.0169 0.05223 0.04455 0.0172 0.0758 1.0000
10.500 1.0150 0.05565 0.04835 0.0195 0.0756 1.0000
10.750 1.0118 0.05956 0.05255 0.0215 0.0760 1.0000
11.000 1.0097 0.06403 0.05722 0.0228 0.0766 1.0000
11.250 1.0058 0.06754 0.06099 0.0246 0.0779 1.0000
11.500 0.8986 0.07469 0.06887 0.0267 0.0820 1.0000
11.750 0.8424 0.08527 0.07967 0.0200 0.0854 1.0000
12.000 0.8251 0.09288 0.08732 0.0164 0.0876 1.0000
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