NPL 9615 AIRFOIL (npl9615-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9615 AIRFOIL (npl9615-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.44 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9615-il-1000000-n5.txt Download as CSV file: xf-npl9615-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9615 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0509 0.06001 0.05733 -0.0395 1.0000 0.0092
-14.750 -1.0775 0.05198 0.04910 -0.0449 1.0000 0.0092
-14.500 -1.0943 0.04655 0.04349 -0.0477 1.0000 0.0092
-14.250 -1.1063 0.04241 0.03918 -0.0489 1.0000 0.0092
-14.000 -1.1146 0.03915 0.03577 -0.0489 1.0000 0.0092
-13.750 -1.1200 0.03654 0.03301 -0.0479 1.0000 0.0092
-13.500 -1.1231 0.03436 0.03068 -0.0463 1.0000 0.0092
-13.250 -1.1237 0.03255 0.02874 -0.0442 1.0000 0.0092
-13.000 -1.1227 0.03099 0.02704 -0.0417 1.0000 0.0092
-12.750 -1.1201 0.02966 0.02558 -0.0389 1.0000 0.0093
-12.500 -1.1148 0.02855 0.02437 -0.0360 1.0000 0.0093
-12.250 -1.1049 0.02755 0.02326 -0.0338 1.0000 0.0094
-12.000 -1.0928 0.02665 0.02226 -0.0318 1.0000 0.0094
-11.750 -1.0785 0.02592 0.02145 -0.0300 1.0000 0.0095
-11.500 -1.0660 0.02497 0.02039 -0.0279 1.0000 0.0096
-11.250 -1.0590 0.02335 0.01857 -0.0251 1.0000 0.0097
-11.000 -1.0466 0.02225 0.01734 -0.0229 1.0000 0.0098
-10.750 -1.0325 0.02130 0.01629 -0.0208 1.0000 0.0098
-10.500 -1.0173 0.02047 0.01536 -0.0188 1.0000 0.0098
-10.250 -1.0010 0.01975 0.01456 -0.0170 1.0000 0.0098
-10.000 -0.9842 0.01908 0.01382 -0.0151 1.0000 0.0098
-9.750 -0.9577 0.01834 0.01300 -0.0154 0.9987 0.0098
-9.500 -0.9303 0.01763 0.01222 -0.0158 0.9965 0.0098
-9.250 -0.9031 0.01696 0.01148 -0.0161 0.9932 0.0098
-9.000 -0.8769 0.01634 0.01080 -0.0162 0.9886 0.0098
-8.750 -0.8527 0.01577 0.01017 -0.0157 0.9834 0.0098
-8.500 -0.8259 0.01521 0.00956 -0.0158 0.9774 0.0098
-8.250 -0.7950 0.01464 0.00894 -0.0168 0.9709 0.0098
-8.000 -0.7602 0.01407 0.00833 -0.0186 0.9655 0.0098
-7.750 -0.7233 0.01352 0.00773 -0.0209 0.9592 0.0097
-7.500 -0.6890 0.01302 0.00718 -0.0225 0.9512 0.0097
-7.250 -0.6564 0.01256 0.00667 -0.0237 0.9410 0.0097
-7.000 -0.6276 0.01218 0.00623 -0.0241 0.9269 0.0097
-6.750 -0.6007 0.01184 0.00582 -0.0240 0.9117 0.0097
-6.500 -0.5748 0.01154 0.00545 -0.0236 0.8966 0.0097
-6.250 -0.5496 0.01126 0.00510 -0.0231 0.8835 0.0097
-6.000 -0.5245 0.01101 0.00478 -0.0225 0.8711 0.0097
-5.750 -0.4993 0.01076 0.00448 -0.0219 0.8585 0.0097
-5.500 -0.4741 0.01053 0.00419 -0.0214 0.8407 0.0097
-5.250 -0.4510 0.01040 0.00391 -0.0203 0.7944 0.0097
-5.000 -0.4266 0.01025 0.00365 -0.0195 0.7757 0.0098
-4.750 -0.4014 0.01010 0.00343 -0.0189 0.7616 0.0098
-4.500 -0.3761 0.00995 0.00322 -0.0184 0.7461 0.0098
-4.250 -0.3509 0.00983 0.00301 -0.0178 0.7227 0.0098
-4.000 -0.3263 0.00976 0.00282 -0.0170 0.6920 0.0098
-3.750 -0.3015 0.00969 0.00265 -0.0164 0.6637 0.0099
-3.500 -0.2761 0.00961 0.00248 -0.0158 0.6404 0.0099
-3.250 -0.2503 0.00953 0.00233 -0.0153 0.6208 0.0099
-3.000 -0.2243 0.00945 0.00219 -0.0149 0.6060 0.0100
-2.750 -0.1980 0.00936 0.00206 -0.0145 0.5924 0.0101
-2.500 -0.1717 0.00928 0.00194 -0.0141 0.5796 0.0102
-2.250 -0.1456 0.00923 0.00183 -0.0137 0.5624 0.0103
-2.000 -0.1196 0.00920 0.00173 -0.0133 0.5428 0.0105
-1.750 -0.0935 0.00917 0.00164 -0.0129 0.5243 0.0108
-1.500 -0.0672 0.00910 0.00155 -0.0125 0.5120 0.0116
-1.250 -0.0410 0.00904 0.00147 -0.0121 0.4986 0.0170
-1.000 -0.0144 0.00901 0.00142 -0.0118 0.4854 0.0189
-0.750 0.0117 0.00896 0.00137 -0.0114 0.4709 0.0278
-0.500 0.0376 0.00899 0.00135 -0.0110 0.4466 0.0318
-0.250 0.0632 0.00906 0.00133 -0.0105 0.4161 0.0351
0.000 0.0888 0.00912 0.00132 -0.0100 0.3890 0.0398
0.250 0.1147 0.00914 0.00132 -0.0096 0.3678 0.0519
0.500 0.1325 0.00834 0.00119 -0.0079 0.3503 0.2978
0.750 0.1481 0.00754 0.00112 -0.0057 0.3315 0.5317
1.000 0.1678 0.00728 0.00115 -0.0041 0.3063 0.6390
1.250 0.1901 0.00720 0.00120 -0.0029 0.2862 0.6973
1.500 0.2124 0.00717 0.00126 -0.0017 0.2610 0.7529
1.750 0.2362 0.00716 0.00132 -0.0007 0.2461 0.7851
2.000 0.2593 0.00713 0.00143 0.0004 0.2363 0.8322
2.250 0.2851 0.00718 0.00151 0.0010 0.2239 0.8614
2.500 0.3111 0.00731 0.00160 0.0014 0.2071 0.8760
2.750 0.3378 0.00743 0.00169 0.0017 0.1940 0.8862
3.000 0.3649 0.00756 0.00179 0.0019 0.1801 0.8954
3.250 0.3918 0.00771 0.00190 0.0021 0.1661 0.9055
3.500 0.4197 0.00788 0.00203 0.0021 0.1496 0.9156
3.750 0.4472 0.00806 0.00216 0.0021 0.1367 0.9267
4.000 0.4777 0.00823 0.00230 0.0015 0.1271 0.9353
4.250 0.5080 0.00838 0.00244 0.0009 0.1201 0.9441
4.750 0.5742 0.00881 0.00278 -0.0016 0.1030 0.9553
5.000 0.6084 0.00904 0.00297 -0.0032 0.0960 0.9596
5.250 0.6417 0.00923 0.00313 -0.0045 0.0897 0.9637
5.500 0.6735 0.00944 0.00330 -0.0055 0.0836 0.9677
5.750 0.7070 0.00962 0.00348 -0.0068 0.0807 0.9704
6.000 0.7397 0.00982 0.00367 -0.0080 0.0739 0.9743
6.250 0.7701 0.01006 0.00391 -0.0087 0.0677 0.9796
6.500 0.7974 0.01039 0.00420 -0.0088 0.0582 0.9848
6.750 0.8247 0.01075 0.00449 -0.0089 0.0472 0.9885
7.000 0.8546 0.01116 0.00483 -0.0096 0.0357 0.9913
7.250 0.8840 0.01156 0.00518 -0.0103 0.0281 0.9940
7.500 0.9138 0.01190 0.00551 -0.0110 0.0243 0.9962
7.750 0.9433 0.01224 0.00584 -0.0117 0.0219 0.9979
8.000 0.9730 0.01257 0.00617 -0.0124 0.0203 0.9992
8.250 1.0005 0.01292 0.00652 -0.0126 0.0191 1.0000
8.500 1.0208 0.01322 0.00684 -0.0112 0.0181 1.0000
8.750 1.0407 0.01355 0.00718 -0.0098 0.0172 1.0000
9.000 1.0607 0.01389 0.00753 -0.0085 0.0165 1.0000
9.250 1.0808 0.01421 0.00788 -0.0071 0.0158 1.0000
9.500 1.1005 0.01457 0.00826 -0.0057 0.0152 1.0000
9.750 1.1198 0.01498 0.00868 -0.0043 0.0146 1.0000
10.000 1.1393 0.01536 0.00909 -0.0029 0.0141 1.0000
10.250 1.1590 0.01573 0.00950 -0.0016 0.0136 1.0000
10.500 1.1783 0.01613 0.00994 -0.0002 0.0131 1.0000
10.750 1.1970 0.01656 0.01040 0.0013 0.0127 1.0000
11.000 1.2148 0.01704 0.01090 0.0028 0.0123 1.0000
11.250 1.2323 0.01752 0.01142 0.0044 0.0120 1.0000
11.500 1.2499 0.01798 0.01193 0.0060 0.0117 1.0000
11.750 1.2669 0.01848 0.01247 0.0076 0.0114 1.0000
12.000 1.2833 0.01899 0.01304 0.0093 0.0112 1.0000
12.250 1.2993 0.01954 0.01363 0.0109 0.0109 1.0000
12.500 1.3136 0.02010 0.01424 0.0129 0.0107 1.0000
12.750 1.3263 0.02070 0.01488 0.0150 0.0106 1.0000
13.000 1.3382 0.02134 0.01558 0.0172 0.0104 1.0000
13.250 1.3497 0.02207 0.01636 0.0192 0.0103 1.0000
13.500 1.3601 0.02289 0.01724 0.0212 0.0101 1.0000
13.750 1.3692 0.02385 0.01826 0.0232 0.0100 1.0000
14.000 1.3785 0.02484 0.01933 0.0249 0.0099 1.0000
14.250 1.3873 0.02592 0.02049 0.0265 0.0098 1.0000
14.500 1.3952 0.02714 0.02178 0.0279 0.0097 1.0000
14.750 1.4021 0.02850 0.02323 0.0291 0.0097 1.0000
15.000 1.4084 0.03001 0.02483 0.0301 0.0096 1.0000
15.250 1.4133 0.03175 0.02666 0.0308 0.0095 1.0000
15.500 1.4174 0.03371 0.02870 0.0313 0.0094 1.0000
15.750 1.4199 0.03593 0.03102 0.0314 0.0093 1.0000
16.000 1.4213 0.03843 0.03362 0.0313 0.0092 1.0000
16.250 1.4208 0.04126 0.03656 0.0309 0.0092 1.0000
16.500 1.4189 0.04442 0.03982 0.0301 0.0091 1.0000
16.750 1.4145 0.04804 0.04355 0.0289 0.0090 1.0000
17.000 1.4081 0.05204 0.04766 0.0275 0.0090 1.0000
17.250 1.3990 0.05657 0.05232 0.0257 0.0089 1.0000
17.500 1.3866 0.06167 0.05753 0.0235 0.0089 1.0000
17.750 1.3717 0.06734 0.06334 0.0210 0.0089 1.0000
18.000 1.3525 0.07380 0.06993 0.0180 0.0088 1.0000
18.250 1.3299 0.08102 0.07729 0.0146 0.0088 1.0000
18.500 1.3043 0.08891 0.08532 0.0108 0.0089 1.0000
18.750 1.2773 0.09728 0.09383 0.0068 0.0089 1.0000
19.000 1.2474 0.10632 0.10302 0.0023 0.0089 1.0000
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Polar data table (+)
Polar graphs
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