NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(2)-415 (naca662415-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.75 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca662415-il-1000000.txt Download as CSV file: xf-naca662415-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6554 0.04961 0.04717 -0.1160 0.9635 0.0140
-13.750 -0.6896 0.04004 0.03707 -0.1232 0.9502 0.0141
-13.500 -0.6951 0.03641 0.03311 -0.1245 0.9335 0.0144
-13.250 -0.7074 0.03361 0.03000 -0.1227 0.9176 0.0145
-13.000 -0.7023 0.03281 0.02905 -0.1211 0.9068 0.0147
-12.750 -0.7267 0.02908 0.02492 -0.1169 0.8946 0.0148
-12.500 -0.7336 0.02661 0.02219 -0.1139 0.8857 0.0151
-12.250 -0.7261 0.02574 0.02123 -0.1119 0.8786 0.0153
-12.000 -0.7175 0.02491 0.02031 -0.1100 0.8723 0.0155
-11.750 -0.7068 0.02460 0.01994 -0.1082 0.8663 0.0157
-11.500 -0.6958 0.02436 0.01966 -0.1062 0.8610 0.0160
-11.250 -0.6861 0.02359 0.01880 -0.1041 0.8558 0.0162
-11.000 -0.6756 0.02302 0.01813 -0.1019 0.8509 0.0164
-10.750 -0.6644 0.02223 0.01721 -0.0997 0.8466 0.0168
-10.500 -0.6507 0.02141 0.01627 -0.0979 0.8427 0.0172
-10.250 -0.6339 0.02054 0.01527 -0.0967 0.8389 0.0175
-10.000 -0.6156 0.01973 0.01431 -0.0956 0.8354 0.0178
-9.750 -0.5967 0.01924 0.01370 -0.0945 0.8320 0.0181
-9.500 -0.5750 0.01781 0.01212 -0.0942 0.8293 0.0187
-9.250 -0.5537 0.01699 0.01127 -0.0936 0.8263 0.0191
-9.000 -0.5335 0.01673 0.01099 -0.0928 0.8232 0.0196
-8.750 -0.5119 0.01626 0.01047 -0.0921 0.8202 0.0199
-8.500 -0.4899 0.01591 0.01004 -0.0915 0.8170 0.0204
-8.250 -0.4674 0.01539 0.00949 -0.0909 0.8147 0.0209
-8.000 -0.4447 0.01491 0.00897 -0.0904 0.8122 0.0214
-7.750 -0.4218 0.01452 0.00853 -0.0898 0.8097 0.0219
-7.500 -0.3988 0.01415 0.00810 -0.0893 0.8073 0.0222
-7.250 -0.3770 0.01357 0.00746 -0.0886 0.8049 0.0228
-7.000 -0.3573 0.01292 0.00678 -0.0876 0.8023 0.0236
-6.750 -0.3345 0.01262 0.00648 -0.0870 0.8002 0.0243
-6.500 -0.3116 0.01230 0.00616 -0.0864 0.7982 0.0250
-6.250 -0.2888 0.01197 0.00581 -0.0858 0.7961 0.0257
-6.000 -0.2656 0.01167 0.00549 -0.0853 0.7940 0.0265
-5.750 -0.2413 0.01145 0.00523 -0.0849 0.7920 0.0271
-5.500 -0.2167 0.01123 0.00499 -0.0846 0.7901 0.0276
-5.250 -0.1972 0.01065 0.00436 -0.0834 0.7881 0.0291
-5.000 -0.1724 0.01045 0.00414 -0.0832 0.7858 0.0305
-4.750 -0.1475 0.01024 0.00393 -0.0829 0.7843 0.0317
-4.500 -0.1222 0.01003 0.00372 -0.0827 0.7826 0.0329
-4.250 -0.0963 0.00987 0.00354 -0.0826 0.7809 0.0338
-4.000 -0.0721 0.00955 0.00321 -0.0822 0.7791 0.0365
-3.750 -0.0461 0.00937 0.00303 -0.0822 0.7775 0.0389
-3.500 -0.0194 0.00924 0.00288 -0.0822 0.7760 0.0411
-3.250 0.0066 0.00904 0.00270 -0.0821 0.7745 0.0473
-3.000 0.0311 0.00870 0.00253 -0.0819 0.7729 0.0900
-2.750 0.0482 0.00766 0.00223 -0.0808 0.7710 0.2979
-2.500 0.0652 0.00642 0.00187 -0.0799 0.7695 0.5439
-2.250 0.0901 0.00603 0.00188 -0.0797 0.7682 0.6676
-2.000 0.1184 0.00604 0.00194 -0.0800 0.7670 0.6938
-1.750 0.1472 0.00608 0.00200 -0.0803 0.7656 0.7093
-1.500 0.1758 0.00615 0.00209 -0.0805 0.7641 0.7239
-1.250 0.2047 0.00622 0.00216 -0.0808 0.7627 0.7345
-1.000 0.2335 0.00631 0.00226 -0.0811 0.7614 0.7421
-0.750 0.2627 0.00639 0.00232 -0.0815 0.7602 0.7485
-0.500 0.2914 0.00645 0.00241 -0.0818 0.7590 0.7544
-0.250 0.3204 0.00654 0.00251 -0.0821 0.7578 0.7598
0.000 0.3499 0.00662 0.00256 -0.0827 0.7565 0.7626
0.250 0.3793 0.00669 0.00260 -0.0832 0.7545 0.7638
0.500 0.4075 0.00661 0.00255 -0.0835 0.7522 0.7654
0.750 0.4360 0.00656 0.00252 -0.0838 0.7492 0.7667
1.000 0.4649 0.00654 0.00250 -0.0842 0.7467 0.7679
1.250 0.4940 0.00654 0.00251 -0.0847 0.7446 0.7691
1.500 0.5230 0.00655 0.00252 -0.0852 0.7424 0.7703
1.750 0.5515 0.00655 0.00252 -0.0855 0.7380 0.7717
2.000 0.5790 0.00649 0.00248 -0.0855 0.7326 0.7731
2.250 0.6072 0.00645 0.00243 -0.0857 0.7271 0.7746
2.500 0.6346 0.00643 0.00242 -0.0858 0.7206 0.7762
2.750 0.6621 0.00640 0.00241 -0.0858 0.7146 0.7777
3.000 0.6897 0.00641 0.00240 -0.0859 0.7076 0.7790
3.250 0.7156 0.00639 0.00237 -0.0856 0.6957 0.7801
3.500 0.7409 0.00636 0.00236 -0.0853 0.6811 0.7820
3.750 0.7659 0.00639 0.00239 -0.0848 0.6652 0.7837
4.000 0.7873 0.00652 0.00244 -0.0836 0.6297 0.7854
4.250 0.7874 0.00735 0.00279 -0.0782 0.5273 0.7877
4.500 0.7874 0.00822 0.00328 -0.0730 0.4411 0.7902
4.750 0.7840 0.00902 0.00371 -0.0672 0.3637 0.7929
5.000 0.7788 0.00989 0.00423 -0.0611 0.2900 0.7955
5.250 0.7751 0.01085 0.00484 -0.0556 0.2142 0.7985
5.500 0.7714 0.01194 0.00556 -0.0504 0.1330 0.8017
5.750 0.7736 0.01294 0.00625 -0.0464 0.0696 0.8046
6.000 0.7848 0.01363 0.00680 -0.0439 0.0420 0.8074
6.250 0.8011 0.01412 0.00726 -0.0423 0.0354 0.8099
6.500 0.8202 0.01450 0.00765 -0.0412 0.0334 0.8122
6.750 0.8379 0.01492 0.00808 -0.0399 0.0311 0.8151
7.000 0.8530 0.01548 0.00869 -0.0382 0.0286 0.8180
7.250 0.8722 0.01586 0.00910 -0.0372 0.0275 0.8209
7.500 0.8907 0.01628 0.00954 -0.0361 0.0262 0.8239
7.750 0.9076 0.01682 0.01008 -0.0348 0.0246 0.8270
8.000 0.9211 0.01754 0.01085 -0.0330 0.0231 0.8302
8.250 0.9391 0.01798 0.01135 -0.0319 0.0225 0.8336
8.500 0.9571 0.01845 0.01186 -0.0308 0.0215 0.8372
8.750 0.9744 0.01899 0.01242 -0.0297 0.0206 0.8410
9.000 0.9905 0.01961 0.01306 -0.0285 0.0197 0.8447
9.250 0.9993 0.02064 0.01416 -0.0262 0.0187 0.8493
9.500 1.0153 0.02126 0.01484 -0.0250 0.0184 0.8538
9.750 1.0316 0.02189 0.01552 -0.0239 0.0180 0.8584
10.000 1.0475 0.02253 0.01622 -0.0227 0.0173 0.8630
10.250 1.0632 0.02316 0.01691 -0.0215 0.0167 0.8682
10.500 1.0778 0.02392 0.01771 -0.0203 0.0164 0.8737
10.750 1.0927 0.02464 0.01847 -0.0191 0.0159 0.8794
11.000 1.1050 0.02551 0.01939 -0.0177 0.0154 0.8860
11.250 1.1094 0.02705 0.02102 -0.0154 0.0149 0.8929
11.500 1.1232 0.02783 0.02189 -0.0141 0.0147 0.9007
11.750 1.1369 0.02864 0.02277 -0.0129 0.0144 0.9091
12.000 1.1481 0.02963 0.02385 -0.0113 0.0143 0.9192
12.250 1.1597 0.03052 0.02483 -0.0098 0.0139 0.9314
12.500 1.1700 0.03149 0.02593 -0.0083 0.0137 0.9500
12.750 1.1890 0.03257 0.02711 -0.0088 0.0134 1.0000
13.000 1.2010 0.03383 0.02844 -0.0079 0.0133 1.0000
13.250 1.2138 0.03501 0.02966 -0.0072 0.0130 1.0000
13.500 1.2261 0.03623 0.03093 -0.0064 0.0128 1.0000
13.750 1.2371 0.03758 0.03233 -0.0056 0.0126 1.0000
14.000 1.2474 0.03901 0.03382 -0.0048 0.0124 1.0000
14.250 1.2571 0.04052 0.03538 -0.0040 0.0123 1.0000
14.500 1.2655 0.04222 0.03716 -0.0032 0.0122 1.0000
14.750 1.2702 0.04448 0.03951 -0.0021 0.0118 1.0000
15.000 1.2742 0.04703 0.04222 -0.0010 0.0117 1.0000
15.250 1.2819 0.04860 0.04387 -0.0006 0.0116 1.0000
15.500 1.2873 0.05068 0.04607 0.0000 0.0115 1.0000
15.750 1.2926 0.05278 0.04828 0.0005 0.0114 1.0000
16.000 1.2943 0.05544 0.05107 0.0011 0.0113 1.0000
16.250 1.2966 0.05798 0.05372 0.0014 0.0112 1.0000
16.500 1.2964 0.06091 0.05680 0.0016 0.0111 1.0000
16.750 1.2956 0.06400 0.06002 0.0016 0.0109 1.0000
17.000 1.2917 0.06761 0.06377 0.0014 0.0109 1.0000
17.250 1.2877 0.07130 0.06759 0.0010 0.0108 1.0000
17.500 1.2792 0.07580 0.07226 0.0002 0.0107 1.0000
17.750 1.2725 0.08018 0.07679 -0.0009 0.0106 1.0000
18.000 1.2602 0.08563 0.08241 -0.0025 0.0106 1.0000
18.250 1.2481 0.09125 0.08819 -0.0046 0.0105 1.0000
18.500 1.2272 0.09867 0.09582 -0.0076 0.0105 1.0000
18.750 1.2107 0.10566 0.10297 -0.0111 0.0105 1.0000
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Polar data table (+)
Polar graphs
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