NACA 65(3)-618 (naca653618-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(3)-618 (naca653618-il) Reynolds number: 500,000 Max Cl/Cd: 105.16 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca653618-il-500000-n5.txt Download as CSV file: xf-naca653618-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(3)-618
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.7321 0.09190 0.08860 -0.0844 1.0000 0.0168
-17.750 -0.7633 0.08253 0.07903 -0.0899 1.0000 0.0168
-17.500 -0.7825 0.07582 0.07218 -0.0937 1.0000 0.0169
-17.250 -0.7940 0.07071 0.06697 -0.0964 1.0000 0.0170
-17.000 -0.8061 0.06577 0.06191 -0.0988 1.0000 0.0171
-16.750 -0.8121 0.06199 0.05805 -0.1005 1.0000 0.0172
-16.500 -0.8157 0.05874 0.05474 -0.1018 1.0000 0.0173
-16.250 -0.8215 0.05542 0.05133 -0.1027 1.0000 0.0174
-16.000 -0.8241 0.05272 0.04856 -0.1033 1.0000 0.0175
-15.750 -0.8200 0.05000 0.04578 -0.1046 0.9928 0.0177
-15.500 -0.8110 0.04706 0.04272 -0.1075 0.9834 0.0180
-15.250 -0.7990 0.04428 0.03982 -0.1107 0.9733 0.0182
-15.000 -0.7825 0.04169 0.03707 -0.1144 0.9648 0.0185
-14.750 -0.7612 0.03915 0.03436 -0.1188 0.9577 0.0189
-14.500 -0.7382 0.03677 0.03179 -0.1231 0.9485 0.0193
-14.250 -0.7122 0.03457 0.02938 -0.1275 0.9386 0.0197
-13.750 -0.6663 0.03130 0.02579 -0.1332 0.9119 0.0204
-13.500 -0.6504 0.03019 0.02459 -0.1339 0.8984 0.0208
-13.250 -0.6368 0.02920 0.02349 -0.1338 0.8858 0.0210
-12.750 -0.6121 0.02736 0.02144 -0.1326 0.8634 0.0216
-12.500 -0.5996 0.02650 0.02046 -0.1318 0.8538 0.0220
-12.250 -0.5868 0.02566 0.01952 -0.1310 0.8449 0.0223
-12.000 -0.5733 0.02486 0.01860 -0.1300 0.8370 0.0226
-11.750 -0.5594 0.02410 0.01773 -0.1291 0.8289 0.0230
-11.250 -0.5302 0.02275 0.01615 -0.1272 0.8139 0.0237
-11.000 -0.5165 0.02196 0.01532 -0.1261 0.8066 0.0241
-10.750 -0.5018 0.02131 0.01461 -0.1251 0.8004 0.0244
-10.500 -0.4866 0.02069 0.01395 -0.1240 0.7940 0.0248
-10.250 -0.4713 0.02011 0.01331 -0.1230 0.7878 0.0251
-10.000 -0.4555 0.01956 0.01270 -0.1219 0.7821 0.0256
-9.750 -0.4396 0.01903 0.01212 -0.1208 0.7758 0.0260
-9.500 -0.4243 0.01850 0.01151 -0.1196 0.7698 0.0264
-9.250 -0.4092 0.01796 0.01091 -0.1183 0.7643 0.0269
-9.000 -0.3944 0.01744 0.01033 -0.1168 0.7586 0.0272
-8.750 -0.3801 0.01700 0.00981 -0.1152 0.7533 0.0276
-8.500 -0.3686 0.01656 0.00931 -0.1132 0.7485 0.0280
-8.250 -0.3554 0.01602 0.00877 -0.1115 0.7434 0.0285
-8.000 -0.3379 0.01562 0.00832 -0.1104 0.7384 0.0290
-7.750 -0.3193 0.01525 0.00789 -0.1094 0.7339 0.0295
-7.500 -0.2994 0.01487 0.00749 -0.1086 0.7293 0.0300
-7.250 -0.2786 0.01452 0.00710 -0.1078 0.7246 0.0306
-7.000 -0.2571 0.01421 0.00673 -0.1072 0.7202 0.0313
-6.500 -0.2115 0.01362 0.00605 -0.1063 0.7127 0.0327
-6.250 -0.1887 0.01327 0.00568 -0.1059 0.7087 0.0336
-6.000 -0.1648 0.01300 0.00539 -0.1056 0.7048 0.0348
-5.750 -0.1401 0.01277 0.00512 -0.1054 0.7011 0.0363
-5.500 -0.1149 0.01256 0.00486 -0.1053 0.6975 0.0378
-5.250 -0.0897 0.01229 0.00460 -0.1052 0.6938 0.0400
-5.000 -0.0639 0.01208 0.00437 -0.1052 0.6900 0.0427
-4.750 -0.0380 0.01186 0.00415 -0.1052 0.6866 0.0469
-4.500 -0.0119 0.01165 0.00394 -0.1052 0.6835 0.0549
-4.250 0.0141 0.01136 0.00373 -0.1053 0.6806 0.0751
-4.000 0.0397 0.01094 0.00349 -0.1055 0.6775 0.1193
-3.750 0.0650 0.01038 0.00321 -0.1059 0.6741 0.1943
-3.500 0.0906 0.00967 0.00288 -0.1065 0.6708 0.3013
-3.250 0.1170 0.00887 0.00256 -0.1073 0.6676 0.4387
-3.000 0.1454 0.00864 0.00254 -0.1079 0.6648 0.5126
-2.750 0.1744 0.00858 0.00259 -0.1083 0.6622 0.5527
-2.500 0.2035 0.00861 0.00266 -0.1087 0.6594 0.5805
-2.250 0.2325 0.00867 0.00273 -0.1090 0.6565 0.5985
-2.000 0.2614 0.00872 0.00277 -0.1093 0.6537 0.6084
-1.750 0.2905 0.00877 0.00273 -0.1098 0.6510 0.6128
-1.500 0.3192 0.00879 0.00272 -0.1101 0.6483 0.6152
-1.250 0.3481 0.00879 0.00273 -0.1104 0.6458 0.6177
-1.000 0.3771 0.00880 0.00274 -0.1108 0.6432 0.6204
-0.750 0.4061 0.00882 0.00274 -0.1112 0.6406 0.6230
-0.500 0.4350 0.00885 0.00275 -0.1116 0.6381 0.6257
-0.250 0.4639 0.00890 0.00276 -0.1120 0.6356 0.6285
0.000 0.4928 0.00894 0.00276 -0.1124 0.6332 0.6310
0.250 0.5215 0.00898 0.00280 -0.1128 0.6308 0.6332
0.500 0.5501 0.00900 0.00285 -0.1131 0.6283 0.6356
0.750 0.5788 0.00904 0.00290 -0.1135 0.6260 0.6381
1.000 0.6074 0.00908 0.00296 -0.1138 0.6236 0.6410
1.250 0.6361 0.00913 0.00301 -0.1142 0.6211 0.6440
1.500 0.6647 0.00919 0.00306 -0.1145 0.6186 0.6468
1.750 0.6932 0.00926 0.00311 -0.1149 0.6162 0.6493
2.000 0.7217 0.00933 0.00320 -0.1152 0.6141 0.6517
2.250 0.7499 0.00937 0.00330 -0.1155 0.6119 0.6543
2.500 0.7781 0.00942 0.00340 -0.1158 0.6093 0.6572
2.750 0.8062 0.00948 0.00350 -0.1160 0.6067 0.6605
3.000 0.8343 0.00956 0.00359 -0.1163 0.6042 0.6639
3.250 0.8625 0.00964 0.00368 -0.1166 0.6017 0.6669
3.500 0.8903 0.00972 0.00379 -0.1168 0.5989 0.6696
3.750 0.9175 0.00979 0.00392 -0.1169 0.5953 0.6726
4.000 0.9441 0.00984 0.00404 -0.1168 0.5906 0.6759
4.250 0.9708 0.00992 0.00415 -0.1168 0.5861 0.6793
4.500 0.9975 0.01002 0.00425 -0.1168 0.5818 0.6829
4.750 1.0227 0.01008 0.00438 -0.1165 0.5749 0.6864
5.000 1.0464 0.01017 0.00448 -0.1159 0.5658 0.6900
5.250 1.0697 0.01025 0.00462 -0.1152 0.5552 0.6938
5.500 1.0915 0.01038 0.00476 -0.1142 0.5428 0.6978
5.750 1.1105 0.01056 0.00491 -0.1127 0.5242 0.7018
6.000 1.1253 0.01083 0.00511 -0.1104 0.5006 0.7055
6.250 1.1348 0.01116 0.00538 -0.1071 0.4720 0.7095
6.500 1.1327 0.01184 0.00587 -0.1018 0.4298 0.7143
6.750 1.1235 0.01295 0.00672 -0.0957 0.3785 0.7195
7.000 1.1172 0.01414 0.00770 -0.0904 0.3350 0.7244
7.250 1.1127 0.01539 0.00878 -0.0858 0.2944 0.7297
7.750 1.1078 0.01813 0.01119 -0.0781 0.2211 0.7406
8.000 1.1069 0.01957 0.01251 -0.0748 0.1882 0.7457
8.250 1.1073 0.02106 0.01387 -0.0719 0.1582 0.7515
8.500 1.1082 0.02261 0.01530 -0.0692 0.1297 0.7573
8.750 1.1097 0.02419 0.01677 -0.0667 0.1036 0.7629
9.000 1.1122 0.02577 0.01827 -0.0645 0.0813 0.7695
9.250 1.1163 0.02734 0.01975 -0.0626 0.0627 0.7761
9.500 1.1223 0.02879 0.02118 -0.0609 0.0485 0.7827
9.750 1.1300 0.03019 0.02257 -0.0594 0.0398 0.7899
10.000 1.1392 0.03152 0.02392 -0.0582 0.0344 0.7968
10.250 1.1493 0.03280 0.02523 -0.0571 0.0309 0.8041
10.500 1.1601 0.03408 0.02656 -0.0561 0.0285 0.8118
10.750 1.1704 0.03539 0.02793 -0.0551 0.0264 0.8196
11.000 1.1809 0.03674 0.02934 -0.0541 0.0248 0.8283
11.250 1.1916 0.03805 0.03073 -0.0532 0.0234 0.8378
11.500 1.2015 0.03945 0.03219 -0.0523 0.0222 0.8477
11.750 1.2100 0.04096 0.03377 -0.0513 0.0212 0.8589
12.000 1.2201 0.04231 0.03522 -0.0503 0.0203 0.8713
12.250 1.2288 0.04377 0.03677 -0.0493 0.0195 0.8862
12.500 1.2367 0.04523 0.03832 -0.0482 0.0189 0.9063
12.750 1.2439 0.04685 0.04003 -0.0472 0.0182 0.9369
13.250 1.2629 0.05025 0.04356 -0.0465 0.0171 1.0000
13.500 1.2724 0.05209 0.04545 -0.0463 0.0165 1.0000
13.750 1.2817 0.05394 0.04735 -0.0460 0.0160 1.0000
14.000 1.2898 0.05596 0.04942 -0.0458 0.0156 1.0000
14.250 1.2973 0.05806 0.05156 -0.0456 0.0153 1.0000
14.500 1.3028 0.06043 0.05397 -0.0454 0.0149 1.0000
14.750 1.3106 0.06258 0.05620 -0.0453 0.0146 1.0000
15.000 1.3177 0.06484 0.05853 -0.0453 0.0143 1.0000
15.250 1.3245 0.06716 0.06092 -0.0454 0.0140 1.0000
15.500 1.3311 0.06953 0.06336 -0.0455 0.0137 1.0000
15.750 1.3369 0.07205 0.06595 -0.0456 0.0134 1.0000
16.000 1.3429 0.07456 0.06853 -0.0458 0.0131 1.0000
16.250 1.3482 0.07721 0.07123 -0.0462 0.0128 1.0000
16.500 1.3526 0.08000 0.07409 -0.0465 0.0126 1.0000
16.750 1.3554 0.08304 0.07719 -0.0470 0.0125 1.0000
17.000 1.3567 0.08630 0.08053 -0.0475 0.0123 1.0000
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