NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)-615 (naca632615-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.64 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632615-il-1000000-n5.txt Download as CSV file: xf-naca632615-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.8139 0.11244 0.10997 -0.0496 1.0000 0.0092
-18.250 -0.8872 0.09498 0.09227 -0.0594 1.0000 0.0089
-18.000 -0.9354 0.08258 0.07967 -0.0666 1.0000 0.0089
-17.750 -0.9701 0.07292 0.06984 -0.0725 1.0000 0.0089
-17.500 -0.9924 0.06568 0.06245 -0.0769 1.0000 0.0089
-17.250 -1.0072 0.05995 0.05661 -0.0803 1.0000 0.0089
-17.000 -1.0223 0.05445 0.05098 -0.0836 1.0000 0.0089
-16.750 -1.0282 0.05053 0.04696 -0.0857 1.0000 0.0091
-16.500 -1.0346 0.04674 0.04307 -0.0876 1.0000 0.0091
-16.250 -1.0395 0.04331 0.03954 -0.0892 1.0000 0.0093
-16.000 -1.0406 0.04046 0.03661 -0.0904 1.0000 0.0094
-15.750 -1.0423 0.03765 0.03371 -0.0913 1.0000 0.0094
-15.500 -1.0405 0.03535 0.03133 -0.0919 1.0000 0.0095
-15.250 -1.0388 0.03316 0.02905 -0.0922 1.0000 0.0096
-15.000 -1.0358 0.03122 0.02705 -0.0923 1.0000 0.0097
-14.750 -1.0326 0.02945 0.02520 -0.0920 1.0000 0.0098
-14.500 -1.0299 0.02783 0.02350 -0.0913 1.0000 0.0099
-14.000 -1.0070 0.02478 0.02031 -0.0925 0.9917 0.0102
-13.750 -0.9864 0.02322 0.01870 -0.0947 0.9819 0.0105
-13.500 -0.9587 0.02192 0.01733 -0.0977 0.9720 0.0108
-13.250 -0.9230 0.02073 0.01606 -0.1019 0.9628 0.0111
-13.000 -0.8845 0.01964 0.01490 -0.1063 0.9510 0.0115
-12.750 -0.8497 0.01869 0.01383 -0.1098 0.9329 0.0119
-12.500 -0.8284 0.01799 0.01299 -0.1103 0.9108 0.0122
-12.250 -0.8105 0.01745 0.01232 -0.1097 0.8941 0.0125
-12.000 -0.7938 0.01685 0.01162 -0.1088 0.8797 0.0128
-11.750 -0.7749 0.01633 0.01103 -0.1081 0.8675 0.0133
-11.500 -0.7546 0.01587 0.01051 -0.1075 0.8569 0.0138
-11.000 -0.7111 0.01503 0.00951 -0.1065 0.8375 0.0147
-10.750 -0.6884 0.01465 0.00905 -0.1061 0.8288 0.0151
-10.500 -0.6650 0.01424 0.00858 -0.1059 0.8205 0.0157
-10.000 -0.6166 0.01352 0.00776 -0.1055 0.8053 0.0170
-9.750 -0.5915 0.01322 0.00740 -0.1053 0.7978 0.0178
-9.500 -0.5658 0.01293 0.00705 -0.1053 0.7914 0.0185
-9.250 -0.5402 0.01259 0.00669 -0.1053 0.7844 0.0194
-9.000 -0.5143 0.01232 0.00637 -0.1052 0.7775 0.0203
-8.750 -0.4876 0.01206 0.00607 -0.1053 0.7711 0.0213
-8.500 -0.4609 0.01182 0.00577 -0.1053 0.7643 0.0220
-8.250 -0.4342 0.01155 0.00547 -0.1054 0.7581 0.0231
-8.000 -0.4069 0.01131 0.00521 -0.1055 0.7515 0.0243
-7.750 -0.3797 0.01112 0.00497 -0.1056 0.7451 0.0255
-7.500 -0.3519 0.01093 0.00473 -0.1058 0.7392 0.0263
-7.250 -0.3244 0.01067 0.00445 -0.1060 0.7325 0.0277
-7.000 -0.2967 0.01048 0.00422 -0.1061 0.7266 0.0290
-6.750 -0.2685 0.01029 0.00401 -0.1064 0.7206 0.0304
-6.500 -0.2404 0.01014 0.00381 -0.1066 0.7141 0.0313
-6.250 -0.2123 0.00993 0.00357 -0.1068 0.7083 0.0331
-6.000 -0.1838 0.00975 0.00338 -0.1071 0.7024 0.0349
-5.750 -0.1554 0.00961 0.00320 -0.1073 0.6961 0.0364
-5.500 -0.1268 0.00945 0.00301 -0.1076 0.6904 0.0384
-5.250 -0.0981 0.00928 0.00284 -0.1079 0.6844 0.0413
-5.000 -0.0695 0.00916 0.00269 -0.1082 0.6787 0.0439
-4.750 -0.0406 0.00900 0.00253 -0.1085 0.6732 0.0493
-4.500 -0.0117 0.00885 0.00239 -0.1089 0.6670 0.0563
-4.250 0.0171 0.00869 0.00225 -0.1092 0.6611 0.0676
-4.000 0.0463 0.00850 0.00211 -0.1097 0.6562 0.0853
-3.750 0.0755 0.00830 0.00198 -0.1101 0.6504 0.1092
-3.500 0.1046 0.00810 0.00185 -0.1106 0.6443 0.1401
-3.250 0.1342 0.00784 0.00172 -0.1112 0.6391 0.1801
-3.000 0.1639 0.00754 0.00159 -0.1119 0.6334 0.2365
-2.750 0.1934 0.00728 0.00148 -0.1126 0.6279 0.2919
-2.500 0.2234 0.00703 0.00139 -0.1133 0.6228 0.3457
-2.250 0.2532 0.00685 0.00134 -0.1139 0.6168 0.3959
-2.000 0.2827 0.00674 0.00132 -0.1144 0.6113 0.4393
-1.750 0.3124 0.00666 0.00132 -0.1148 0.6066 0.4715
-1.500 0.3419 0.00663 0.00132 -0.1152 0.6011 0.4895
-1.250 0.3710 0.00665 0.00133 -0.1155 0.5954 0.5032
-1.000 0.4005 0.00664 0.00135 -0.1158 0.5905 0.5175
-0.750 0.4298 0.00665 0.00136 -0.1161 0.5853 0.5269
-0.500 0.4589 0.00669 0.00138 -0.1164 0.5799 0.5348
-0.250 0.4880 0.00671 0.00140 -0.1167 0.5749 0.5419
0.000 0.5173 0.00674 0.00143 -0.1170 0.5696 0.5493
0.500 0.5752 0.00682 0.00150 -0.1174 0.5592 0.5621
0.750 0.6044 0.00686 0.00154 -0.1177 0.5537 0.5684
1.000 0.6331 0.00692 0.00159 -0.1179 0.5478 0.5737
1.250 0.6619 0.00697 0.00164 -0.1182 0.5424 0.5799
1.500 0.6909 0.00702 0.00170 -0.1184 0.5366 0.5860
1.750 0.7194 0.00710 0.00176 -0.1186 0.5306 0.5912
2.000 0.7482 0.00715 0.00183 -0.1188 0.5254 0.5970
2.250 0.7769 0.00721 0.00191 -0.1190 0.5195 0.6035
2.500 0.8051 0.00730 0.00199 -0.1191 0.5132 0.6092
2.750 0.8337 0.00736 0.00207 -0.1193 0.5062 0.6152
3.250 0.8896 0.00758 0.00227 -0.1195 0.4861 0.6271
3.500 0.9173 0.00770 0.00238 -0.1196 0.4767 0.6338
3.750 0.9449 0.00783 0.00250 -0.1196 0.4664 0.6404
4.000 0.9719 0.00799 0.00264 -0.1195 0.4510 0.6461
4.250 0.9978 0.00824 0.00281 -0.1193 0.4290 0.6527
4.500 1.0236 0.00849 0.00299 -0.1191 0.4062 0.6595
4.750 1.0482 0.00882 0.00322 -0.1187 0.3786 0.6661
5.000 1.0706 0.00933 0.00355 -0.1179 0.3376 0.6730
5.250 1.0910 0.00998 0.00396 -0.1168 0.2900 0.6791
5.500 1.1119 0.01056 0.00436 -0.1159 0.2497 0.6862
5.750 1.1317 0.01121 0.00482 -0.1148 0.2099 0.6934
6.000 1.1521 0.01179 0.00525 -0.1137 0.1775 0.6998
6.250 1.1718 0.01238 0.00571 -0.1126 0.1468 0.7070
6.500 1.1915 0.01295 0.00615 -0.1114 0.1221 0.7140
6.750 1.2108 0.01349 0.00661 -0.1102 0.1002 0.7215
7.000 1.2293 0.01406 0.00708 -0.1088 0.0807 0.7287
7.250 1.2476 0.01460 0.00756 -0.1074 0.0654 0.7359
7.750 1.2813 0.01558 0.00849 -0.1041 0.0457 0.7514
8.250 1.3107 0.01655 0.00946 -0.1000 0.0344 0.7680
8.750 1.3411 0.01754 0.01052 -0.0964 0.0294 0.7862
9.000 1.3551 0.01811 0.01112 -0.0945 0.0274 0.7963
9.250 1.3703 0.01865 0.01172 -0.0929 0.0262 0.8066
9.500 1.3844 0.01926 0.01238 -0.0912 0.0248 0.8178
9.750 1.3975 0.01995 0.01312 -0.0894 0.0235 0.8303
10.000 1.4106 0.02066 0.01389 -0.0877 0.0224 0.8441
10.250 1.4238 0.02137 0.01468 -0.0861 0.0213 0.8597
10.500 1.4353 0.02215 0.01555 -0.0844 0.0203 0.8806
10.750 1.4436 0.02297 0.01648 -0.0821 0.0193 0.9172
11.000 1.4524 0.02378 0.01740 -0.0800 0.0185 1.0000
11.250 1.4653 0.02476 0.01841 -0.0788 0.0175 1.0000
11.500 1.4771 0.02584 0.01952 -0.0776 0.0164 1.0000
11.750 1.4875 0.02706 0.02076 -0.0764 0.0154 1.0000
12.000 1.4989 0.02824 0.02199 -0.0753 0.0146 1.0000
12.250 1.5093 0.02954 0.02331 -0.0743 0.0136 1.0000
12.500 1.5186 0.03097 0.02477 -0.0732 0.0127 1.0000
12.750 1.5281 0.03241 0.02626 -0.0722 0.0121 1.0000
13.000 1.5370 0.03395 0.02784 -0.0713 0.0115 1.0000
13.250 1.5452 0.03559 0.02952 -0.0705 0.0110 1.0000
13.500 1.5525 0.03735 0.03132 -0.0697 0.0104 1.0000
13.750 1.5595 0.03919 0.03321 -0.0689 0.0101 1.0000
14.000 1.5666 0.04107 0.03515 -0.0683 0.0099 1.0000
14.250 1.5734 0.04303 0.03718 -0.0677 0.0097 1.0000
14.500 1.5798 0.04510 0.03930 -0.0672 0.0094 1.0000
14.750 1.5856 0.04727 0.04153 -0.0668 0.0093 1.0000
15.000 1.5905 0.04959 0.04392 -0.0665 0.0090 1.0000
15.250 1.5952 0.05200 0.04640 -0.0663 0.0089 1.0000
15.500 1.5997 0.05450 0.04896 -0.0662 0.0087 1.0000
15.750 1.6031 0.05718 0.05171 -0.0661 0.0086 1.0000
16.000 1.6057 0.06001 0.05461 -0.0662 0.0084 1.0000
16.250 1.6078 0.06298 0.05765 -0.0664 0.0083 1.0000
16.500 1.6091 0.06614 0.06088 -0.0667 0.0082 1.0000
16.750 1.6092 0.06951 0.06433 -0.0671 0.0080 1.0000
17.000 1.6109 0.07273 0.06764 -0.0676 0.0079 1.0000
17.250 1.6119 0.07610 0.07110 -0.0683 0.0079 1.0000
17.500 1.6127 0.07956 0.07464 -0.0690 0.0078 1.0000
17.750 1.6122 0.08328 0.07846 -0.0699 0.0077 1.0000
18.000 1.6109 0.08717 0.08244 -0.0709 0.0077 1.0000
18.250 1.6091 0.09120 0.08656 -0.0721 0.0076 1.0000
18.500 1.6071 0.09534 0.09079 -0.0734 0.0075 1.0000
18.750 1.6043 0.09965 0.09520 -0.0748 0.0075 1.0000
19.000 1.6004 0.10420 0.09984 -0.0764 0.0074 1.0000
19.250 1.5962 0.10883 0.10458 -0.0782 0.0074 1.0000
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