NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)-615 (naca632615-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.4 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca632615-il-1000000.txt Download as CSV file: xf-naca632615-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-615
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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.7552 0.10643 0.10419 -0.0529 1.0000 0.0125
-17.250 -0.8168 0.09042 0.08794 -0.0621 1.0000 0.0124
-17.000 -0.8536 0.07983 0.07718 -0.0685 1.0000 0.0123
-16.750 -0.8735 0.07254 0.06975 -0.0730 1.0000 0.0124
-16.500 -0.8913 0.06591 0.06299 -0.0771 1.0000 0.0124
-16.250 -0.9083 0.05982 0.05676 -0.0808 1.0000 0.0124
-16.000 -0.9183 0.05502 0.05184 -0.0836 1.0000 0.0125
-15.750 -0.9283 0.05057 0.04728 -0.0860 1.0000 0.0126
-15.500 -0.9337 0.04692 0.04353 -0.0879 1.0000 0.0127
-15.250 -0.9394 0.04344 0.03994 -0.0894 1.0000 0.0127
-15.000 -0.9421 0.04045 0.03685 -0.0905 1.0000 0.0129
-14.750 -0.9420 0.03792 0.03423 -0.0912 1.0000 0.0130
-14.500 -0.9445 0.03529 0.03149 -0.0917 1.0000 0.0131
-14.250 -0.9433 0.03319 0.02931 -0.0917 1.0000 0.0132
-14.000 -0.9391 0.03154 0.02758 -0.0914 1.0000 0.0134
-13.750 -0.9385 0.02982 0.02577 -0.0906 1.0000 0.0134
-13.500 -0.9402 0.02822 0.02410 -0.0892 1.0000 0.0135
-13.000 -0.9266 0.02400 0.01971 -0.0913 0.9951 0.0142
-12.750 -0.9016 0.02267 0.01832 -0.0938 0.9882 0.0145
-12.500 -0.8723 0.02153 0.01713 -0.0967 0.9830 0.0149
-12.250 -0.8449 0.02046 0.01599 -0.0989 0.9741 0.0153
-12.000 -0.8094 0.01948 0.01492 -0.1024 0.9700 0.0158
-11.750 -0.7763 0.01865 0.01400 -0.1049 0.9613 0.0162
-11.500 -0.7427 0.01763 0.01288 -0.1078 0.9517 0.0168
-11.250 -0.7132 0.01671 0.01189 -0.1097 0.9377 0.0175
-11.000 -0.6867 0.01624 0.01134 -0.1103 0.9232 0.0181
-10.500 -0.6415 0.01539 0.01032 -0.1096 0.8968 0.0193
-10.250 -0.6185 0.01503 0.00985 -0.1092 0.8861 0.0198
-9.750 -0.5753 0.01393 0.00862 -0.1083 0.8658 0.0213
-9.500 -0.5506 0.01365 0.00828 -0.1080 0.8571 0.0222
-9.250 -0.5255 0.01336 0.00793 -0.1079 0.8487 0.0231
-9.000 -0.4996 0.01317 0.00765 -0.1077 0.8407 0.0238
-8.750 -0.4762 0.01256 0.00701 -0.1075 0.8327 0.0251
-8.500 -0.4503 0.01231 0.00672 -0.1074 0.8253 0.0263
-8.250 -0.4238 0.01205 0.00641 -0.1074 0.8181 0.0274
-8.000 -0.3970 0.01187 0.00616 -0.1074 0.8109 0.0283
-7.750 -0.3715 0.01136 0.00562 -0.1075 0.8042 0.0300
-7.500 -0.3444 0.01112 0.00535 -0.1076 0.7972 0.0315
-7.250 -0.3172 0.01095 0.00512 -0.1076 0.7907 0.0329
-7.000 -0.2897 0.01064 0.00478 -0.1078 0.7843 0.0344
-6.750 -0.2625 0.01032 0.00442 -0.1080 0.7776 0.0364
-6.500 -0.2346 0.01013 0.00420 -0.1081 0.7715 0.0382
-6.250 -0.2063 0.00997 0.00400 -0.1083 0.7649 0.0397
-6.000 -0.1786 0.00965 0.00364 -0.1086 0.7586 0.0427
-5.750 -0.1501 0.00946 0.00343 -0.1088 0.7526 0.0453
-5.500 -0.1217 0.00927 0.00321 -0.1091 0.7461 0.0481
-5.250 -0.0933 0.00906 0.00298 -0.1094 0.7402 0.0529
-5.000 -0.0644 0.00884 0.00278 -0.1097 0.7342 0.0601
-4.750 -0.0358 0.00860 0.00257 -0.1101 0.7279 0.0746
-4.500 -0.0069 0.00827 0.00236 -0.1106 0.7220 0.1087
-4.250 0.0223 0.00788 0.00215 -0.1113 0.7159 0.1601
-4.000 0.0515 0.00746 0.00195 -0.1120 0.7099 0.2268
-3.750 0.0813 0.00695 0.00175 -0.1129 0.7041 0.3166
-3.500 0.1111 0.00662 0.00163 -0.1137 0.6979 0.3904
-3.250 0.1404 0.00651 0.00157 -0.1141 0.6920 0.4279
-3.000 0.1701 0.00642 0.00154 -0.1145 0.6865 0.4535
-2.750 0.1995 0.00639 0.00151 -0.1149 0.6804 0.4735
-2.500 0.2287 0.00638 0.00149 -0.1151 0.6745 0.4890
-2.250 0.2584 0.00635 0.00147 -0.1155 0.6688 0.5027
-2.000 0.2877 0.00634 0.00148 -0.1158 0.6630 0.5211
-1.750 0.3169 0.00636 0.00149 -0.1161 0.6574 0.5374
-1.500 0.3464 0.00635 0.00149 -0.1164 0.6516 0.5473
-1.000 0.4047 0.00640 0.00152 -0.1169 0.6403 0.5678
-0.750 0.4341 0.00642 0.00153 -0.1172 0.6346 0.5757
-0.500 0.4630 0.00645 0.00155 -0.1174 0.6287 0.5828
-0.250 0.4922 0.00650 0.00157 -0.1177 0.6234 0.5898
0.000 0.5215 0.00651 0.00160 -0.1180 0.6177 0.5967
0.250 0.5503 0.00656 0.00163 -0.1182 0.6119 0.6036
0.500 0.5794 0.00660 0.00167 -0.1185 0.6065 0.6098
0.750 0.6085 0.00662 0.00171 -0.1187 0.6008 0.6164
1.000 0.6371 0.00670 0.00175 -0.1189 0.5948 0.6229
1.250 0.6662 0.00673 0.00180 -0.1192 0.5894 0.6290
1.500 0.6951 0.00677 0.00186 -0.1194 0.5834 0.6355
1.750 0.7234 0.00688 0.00192 -0.1195 0.5775 0.6420
2.000 0.7526 0.00689 0.00199 -0.1198 0.5722 0.6484
2.250 0.7812 0.00695 0.00206 -0.1200 0.5663 0.6550
2.500 0.8095 0.00705 0.00214 -0.1201 0.5604 0.6615
2.750 0.8383 0.00708 0.00222 -0.1204 0.5540 0.6684
3.000 0.8661 0.00720 0.00231 -0.1204 0.5462 0.6752
3.250 0.8947 0.00724 0.00239 -0.1206 0.5387 0.6816
3.500 0.9225 0.00735 0.00249 -0.1207 0.5309 0.6886
3.750 0.9509 0.00742 0.00259 -0.1208 0.5237 0.6955
4.000 0.9783 0.00754 0.00271 -0.1208 0.5144 0.7025
4.250 1.0061 0.00764 0.00281 -0.1209 0.5031 0.7097
4.500 1.0333 0.00776 0.00294 -0.1208 0.4911 0.7163
4.750 1.0601 0.00792 0.00308 -0.1207 0.4783 0.7238
5.000 1.0866 0.00810 0.00323 -0.1205 0.4627 0.7309
5.250 1.1128 0.00828 0.00340 -0.1204 0.4472 0.7381
5.750 1.1646 0.00871 0.00378 -0.1199 0.4147 0.7528
6.000 1.1894 0.00900 0.00401 -0.1195 0.3920 0.7606
6.250 1.2121 0.00940 0.00431 -0.1187 0.3615 0.7679
6.500 1.2321 0.01001 0.00472 -0.1176 0.3197 0.7761
6.750 1.2495 0.01076 0.00525 -0.1161 0.2712 0.7840
7.000 1.2649 0.01163 0.00585 -0.1142 0.2207 0.7927
7.250 1.2796 0.01247 0.00647 -0.1123 0.1769 0.8011
7.500 1.2939 0.01329 0.00709 -0.1103 0.1405 0.8107
7.750 1.3082 0.01402 0.00769 -0.1082 0.1121 0.8203
8.000 1.3218 0.01472 0.00828 -0.1061 0.0898 0.8306
8.250 1.3329 0.01532 0.00883 -0.1034 0.0732 0.8425
8.500 1.3419 0.01599 0.00946 -0.1004 0.0591 0.8560
8.750 1.3512 0.01665 0.01011 -0.0975 0.0490 0.8719
9.250 1.3695 0.01781 0.01139 -0.0918 0.0389 0.9222
9.500 1.3765 0.01836 0.01202 -0.0887 0.0361 1.0000
9.750 1.3895 0.01915 0.01281 -0.0870 0.0334 1.0000
10.000 1.4035 0.01990 0.01359 -0.0856 0.0315 1.0000
10.250 1.4150 0.02083 0.01453 -0.0839 0.0296 1.0000
10.500 1.4268 0.02179 0.01551 -0.0824 0.0280 1.0000
10.750 1.4403 0.02265 0.01642 -0.0811 0.0268 1.0000
11.000 1.4516 0.02370 0.01748 -0.0797 0.0254 1.0000
11.250 1.4589 0.02507 0.01888 -0.0780 0.0237 1.0000
11.500 1.4723 0.02605 0.01991 -0.0769 0.0228 1.0000
11.750 1.4835 0.02722 0.02112 -0.0758 0.0216 1.0000
12.000 1.4915 0.02868 0.02259 -0.0745 0.0203 1.0000
12.250 1.4995 0.03020 0.02416 -0.0732 0.0192 1.0000
12.500 1.5099 0.03155 0.02557 -0.0723 0.0183 1.0000
12.750 1.5188 0.03307 0.02712 -0.0713 0.0174 1.0000
13.000 1.5240 0.03495 0.02903 -0.0702 0.0166 1.0000
13.250 1.5287 0.03694 0.03110 -0.0692 0.0159 1.0000
13.500 1.5374 0.03862 0.03283 -0.0685 0.0154 1.0000
13.750 1.5453 0.04040 0.03467 -0.0679 0.0149 1.0000
14.000 1.5520 0.04236 0.03667 -0.0673 0.0143 1.0000
14.250 1.5572 0.04452 0.03889 -0.0668 0.0139 1.0000
14.500 1.5587 0.04717 0.04160 -0.0663 0.0134 1.0000
14.750 1.5579 0.05016 0.04467 -0.0658 0.0131 1.0000
15.000 1.5634 0.05251 0.04710 -0.0656 0.0129 1.0000
15.250 1.5683 0.05499 0.04965 -0.0655 0.0126 1.0000
15.500 1.5718 0.05769 0.05243 -0.0655 0.0124 1.0000
15.750 1.5746 0.06053 0.05534 -0.0656 0.0121 1.0000
16.000 1.5769 0.06352 0.05842 -0.0658 0.0119 1.0000
16.250 1.5790 0.06660 0.06157 -0.0662 0.0117 1.0000
16.500 1.5804 0.06983 0.06487 -0.0666 0.0115 1.0000
16.750 1.5805 0.07329 0.06841 -0.0672 0.0113 1.0000
17.000 1.5789 0.07708 0.07229 -0.0679 0.0112 1.0000
17.250 1.5760 0.08115 0.07644 -0.0688 0.0110 1.0000
17.500 1.5709 0.08564 0.08102 -0.0700 0.0108 1.0000
17.750 1.5630 0.09063 0.08611 -0.0714 0.0107 1.0000
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