NACA 64(3)-618 (naca643618-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64(3)-618 (naca643618-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.33 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca643618-il-1000000.txt Download as CSV file: xf-naca643618-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(3)-618
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
------ -------- --------- --------- -------- -------- --------
-19.750 -0.9089 0.09708 0.09407 -0.0703 1.0000 0.0177
-19.500 -0.9248 0.09089 0.08778 -0.0737 1.0000 0.0178
-19.250 -0.9364 0.08543 0.08222 -0.0767 1.0000 0.0179
-19.000 -0.9464 0.08037 0.07708 -0.0795 1.0000 0.0180
-18.750 -0.9526 0.07597 0.07260 -0.0818 1.0000 0.0181
-18.500 -0.9577 0.07181 0.06837 -0.0840 1.0000 0.0183
-18.250 -0.9630 0.06776 0.06425 -0.0861 1.0000 0.0184
-18.000 -0.9634 0.06441 0.06084 -0.0878 1.0000 0.0186
-17.750 -0.9664 0.06090 0.05725 -0.0894 1.0000 0.0188
-17.500 -0.9678 0.05768 0.05396 -0.0907 1.0000 0.0189
-17.250 -0.9669 0.05481 0.05102 -0.0919 1.0000 0.0191
-17.000 -0.9661 0.05203 0.04817 -0.0930 1.0000 0.0193
-16.750 -0.9647 0.04942 0.04548 -0.0938 1.0000 0.0195
-16.500 -0.9610 0.04712 0.04310 -0.0945 1.0000 0.0198
-16.250 -0.9584 0.04482 0.04072 -0.0950 1.0000 0.0200
-16.000 -0.9526 0.04286 0.03869 -0.0954 1.0000 0.0203
-15.750 -0.9466 0.04106 0.03682 -0.0957 1.0000 0.0204
-15.500 -0.9436 0.03913 0.03482 -0.0956 1.0000 0.0206
-15.250 -0.9469 0.03683 0.03246 -0.0950 1.0000 0.0210
-15.000 -0.9449 0.03507 0.03068 -0.0945 1.0000 0.0213
-14.750 -0.9416 0.03356 0.02913 -0.0936 1.0000 0.0215
-14.500 -0.9383 0.03221 0.02777 -0.0925 1.0000 0.0217
-14.250 -0.9161 0.03073 0.02625 -0.0949 0.9985 0.0221
-14.000 -0.8937 0.02932 0.02480 -0.0969 0.9873 0.0225
-13.750 -0.8687 0.02790 0.02332 -0.0995 0.9775 0.0229
-13.250 -0.7989 0.02545 0.02071 -0.1077 0.9604 0.0239
-13.000 -0.7597 0.02379 0.01897 -0.1134 0.9524 0.0246
-12.750 -0.7190 0.02236 0.01748 -0.1190 0.9387 0.0252
-12.500 -0.6864 0.02148 0.01650 -0.1222 0.9188 0.0258
-12.250 -0.6675 0.02080 0.01571 -0.1223 0.8986 0.0264
-12.000 -0.6542 0.02009 0.01489 -0.1214 0.8815 0.0268
-11.750 -0.6410 0.01945 0.01413 -0.1202 0.8668 0.0273
-11.500 -0.6276 0.01881 0.01342 -0.1191 0.8543 0.0277
-11.250 -0.6134 0.01824 0.01276 -0.1179 0.8433 0.0280
-11.000 -0.6081 0.01726 0.01169 -0.1159 0.8318 0.0286
-10.750 -0.5987 0.01651 0.01090 -0.1142 0.8221 0.0292
-10.500 -0.5885 0.01593 0.01025 -0.1123 0.8127 0.0297
-10.250 -0.5796 0.01544 0.00972 -0.1101 0.8042 0.0303
-10.000 -0.5648 0.01500 0.00920 -0.1088 0.7959 0.0309
-9.750 -0.5463 0.01458 0.00874 -0.1079 0.7889 0.0315
-9.500 -0.5258 0.01425 0.00834 -0.1071 0.7816 0.0321
-9.250 -0.5055 0.01388 0.00790 -0.1064 0.7748 0.0326
-9.000 -0.4867 0.01330 0.00730 -0.1056 0.7683 0.0338
-8.750 -0.4641 0.01298 0.00694 -0.1052 0.7616 0.0349
-8.500 -0.4403 0.01268 0.00660 -0.1048 0.7555 0.0359
-8.250 -0.4156 0.01241 0.00629 -0.1046 0.7492 0.0369
-8.000 -0.3917 0.01209 0.00590 -0.1044 0.7427 0.0379
-7.750 -0.3673 0.01172 0.00552 -0.1042 0.7367 0.0396
-7.500 -0.3414 0.01148 0.00526 -0.1042 0.7303 0.0414
-7.250 -0.3153 0.01129 0.00501 -0.1041 0.7238 0.0428
-7.000 -0.2895 0.01095 0.00466 -0.1041 0.7179 0.0455
-6.750 -0.2627 0.01073 0.00442 -0.1042 0.7117 0.0482
-6.500 -0.2362 0.01049 0.00415 -0.1042 0.7056 0.0519
-6.250 -0.2087 0.01028 0.00394 -0.1044 0.7002 0.0563
-6.000 -0.1814 0.01001 0.00370 -0.1047 0.6943 0.0643
-5.750 -0.1544 0.00976 0.00346 -0.1048 0.6883 0.0766
-5.500 -0.1266 0.00947 0.00325 -0.1052 0.6831 0.0946
-5.250 -0.0988 0.00915 0.00303 -0.1056 0.6774 0.1206
-5.000 -0.0713 0.00880 0.00280 -0.1060 0.6716 0.1590
-4.750 -0.0432 0.00833 0.00254 -0.1066 0.6665 0.2183
-4.500 -0.0148 0.00767 0.00223 -0.1075 0.6612 0.3099
-4.250 0.0140 0.00708 0.00200 -0.1085 0.6557 0.4170
-4.000 0.0433 0.00699 0.00196 -0.1089 0.6505 0.4540
-3.750 0.0731 0.00694 0.00193 -0.1094 0.6457 0.4709
-3.500 0.1026 0.00694 0.00190 -0.1098 0.6404 0.4828
-3.250 0.1316 0.00698 0.00189 -0.1100 0.6349 0.4928
-3.000 0.1614 0.00695 0.00187 -0.1105 0.6304 0.5011
-2.750 0.1910 0.00697 0.00187 -0.1108 0.6254 0.5100
-2.500 0.2202 0.00699 0.00187 -0.1112 0.6205 0.5184
-2.250 0.2494 0.00704 0.00188 -0.1115 0.6159 0.5257
-2.000 0.2792 0.00705 0.00189 -0.1119 0.6118 0.5344
-1.750 0.3087 0.00710 0.00194 -0.1122 0.6074 0.5445
-1.500 0.3378 0.00716 0.00195 -0.1125 0.6030 0.5494
-1.250 0.3669 0.00717 0.00196 -0.1129 0.5987 0.5532
-1.000 0.3965 0.00717 0.00197 -0.1133 0.5952 0.5568
-0.750 0.4259 0.00720 0.00199 -0.1136 0.5913 0.5604
-0.500 0.4551 0.00725 0.00200 -0.1139 0.5873 0.5636
-0.250 0.4839 0.00734 0.00203 -0.1142 0.5831 0.5661
0.000 0.5133 0.00733 0.00205 -0.1146 0.5801 0.5698
0.250 0.5428 0.00733 0.00207 -0.1150 0.5768 0.5731
0.500 0.5719 0.00736 0.00211 -0.1154 0.5732 0.5764
0.750 0.6008 0.00742 0.00215 -0.1156 0.5697 0.5797
1.000 0.6295 0.00752 0.00221 -0.1159 0.5659 0.5828
1.250 0.6588 0.00755 0.00225 -0.1163 0.5633 0.5861
1.500 0.6881 0.00756 0.00231 -0.1167 0.5607 0.5904
1.750 0.7173 0.00760 0.00237 -0.1170 0.5579 0.5946
2.000 0.7461 0.00766 0.00243 -0.1173 0.5547 0.5989
2.250 0.7745 0.00775 0.00250 -0.1175 0.5509 0.6026
2.500 0.8031 0.00782 0.00258 -0.1178 0.5471 0.6072
2.750 0.8321 0.00784 0.00266 -0.1181 0.5444 0.6119
3.000 0.8610 0.00789 0.00273 -0.1185 0.5416 0.6166
3.250 0.8897 0.00796 0.00281 -0.1187 0.5387 0.6210
3.500 0.9180 0.00803 0.00291 -0.1190 0.5357 0.6261
3.750 0.9458 0.00816 0.00303 -0.1191 0.5312 0.6313
4.000 0.9743 0.00817 0.00310 -0.1193 0.5272 0.6367
4.250 1.0024 0.00822 0.00317 -0.1195 0.5221 0.6416
4.500 1.0294 0.00832 0.00328 -0.1195 0.5161 0.6475
4.750 1.0572 0.00837 0.00338 -0.1196 0.5101 0.6535
5.000 1.0849 0.00844 0.00347 -0.1197 0.5048 0.6590
5.250 1.1116 0.00856 0.00360 -0.1196 0.4994 0.6653
5.500 1.1390 0.00862 0.00372 -0.1197 0.4928 0.6719
5.750 1.1647 0.00876 0.00384 -0.1194 0.4832 0.6781
6.000 1.1915 0.00885 0.00398 -0.1194 0.4752 0.6849
6.250 1.2172 0.00899 0.00414 -0.1192 0.4672 0.6917
6.500 1.2433 0.00912 0.00429 -0.1190 0.4591 0.6980
6.750 1.2672 0.00931 0.00448 -0.1185 0.4470 0.7049
7.000 1.2908 0.00952 0.00469 -0.1179 0.4311 0.7120
7.250 1.3089 0.00994 0.00499 -0.1163 0.3953 0.7187
7.500 1.3140 0.01088 0.00564 -0.1126 0.3395 0.7260
7.750 1.3151 0.01177 0.00629 -0.1081 0.2947 0.7333
8.000 1.3126 0.01277 0.00708 -0.1031 0.2515 0.7410
8.250 1.3137 0.01371 0.00787 -0.0990 0.2182 0.7493
8.500 1.3157 0.01467 0.00871 -0.0952 0.1910 0.7572
8.750 1.3187 0.01566 0.00960 -0.0918 0.1663 0.7661
9.000 1.3217 0.01673 0.01059 -0.0886 0.1451 0.7747
9.250 1.3252 0.01785 0.01166 -0.0857 0.1259 0.7845
9.500 1.3291 0.01904 0.01280 -0.0830 0.1101 0.7942
9.750 1.3335 0.02028 0.01401 -0.0806 0.0964 0.8051
10.000 1.3378 0.02159 0.01530 -0.0783 0.0840 0.8163
10.250 1.3436 0.02288 0.01659 -0.0763 0.0741 0.8280
10.750 1.3544 0.02566 0.01939 -0.0725 0.0570 0.8555
11.000 1.3599 0.02706 0.02084 -0.0708 0.0505 0.8732
11.250 1.3642 0.02846 0.02231 -0.0688 0.0454 0.8996
11.500 1.3664 0.02980 0.02378 -0.0666 0.0411 1.0000
11.750 1.3735 0.03146 0.02543 -0.0656 0.0373 1.0000
12.000 1.3824 0.03299 0.02699 -0.0647 0.0346 1.0000
12.250 1.3886 0.03480 0.02880 -0.0638 0.0320 1.0000
12.500 1.3976 0.03641 0.03044 -0.0631 0.0302 1.0000
12.750 1.4050 0.03820 0.03224 -0.0623 0.0284 1.0000
13.000 1.4116 0.04012 0.03419 -0.0617 0.0268 1.0000
13.250 1.4205 0.04185 0.03596 -0.0611 0.0254 1.0000
13.500 1.4265 0.04389 0.03803 -0.0606 0.0241 1.0000
13.750 1.4327 0.04598 0.04015 -0.0601 0.0229 1.0000
14.000 1.4413 0.04785 0.04206 -0.0598 0.0218 1.0000
14.250 1.4476 0.05000 0.04425 -0.0595 0.0208 1.0000
14.500 1.4505 0.05255 0.04683 -0.0591 0.0198 1.0000
14.750 1.4591 0.05454 0.04888 -0.0590 0.0191 1.0000
15.000 1.4666 0.05667 0.05105 -0.0589 0.0184 1.0000
15.250 1.4719 0.05910 0.05352 -0.0588 0.0177 1.0000
15.500 1.4753 0.06176 0.05622 -0.0588 0.0170 1.0000
15.750 1.4778 0.06462 0.05914 -0.0588 0.0166 1.0000
16.000 1.4847 0.06696 0.06154 -0.0590 0.0162 1.0000
16.250 1.4900 0.06955 0.06419 -0.0592 0.0157 1.0000
16.500 1.4956 0.07213 0.06683 -0.0595 0.0153 1.0000
16.750 1.4992 0.07500 0.06975 -0.0598 0.0150 1.0000
17.000 1.5028 0.07788 0.07269 -0.0603 0.0147 1.0000
17.250 1.5027 0.08136 0.07622 -0.0608 0.0143 1.0000
17.500 1.4991 0.08537 0.08031 -0.0616 0.0139 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64(3)-618 (naca643618-il)