NACA 65(3)-618 (naca653618-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(3)-618 (naca653618-il) Reynolds number: 500,000 Max Cl/Cd: 110.34 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca653618-il-500000.txt Download as CSV file: xf-naca653618-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5409 0.08503 0.08234 -0.0897 1.0000 0.0254
-14.750 -0.5659 0.07892 0.07621 -0.0916 1.0000 0.0252
-14.500 -0.6006 0.06798 0.06503 -0.1010 0.9971 0.0251
-14.250 -0.6271 0.05962 0.05641 -0.1082 0.9883 0.0250
-14.000 -0.6454 0.05298 0.04951 -0.1137 0.9813 0.0250
-13.750 -0.6637 0.04703 0.04318 -0.1190 0.9723 0.0252
-13.500 -0.6690 0.04259 0.03837 -0.1241 0.9641 0.0255
-13.250 -0.6582 0.03822 0.03380 -0.1280 0.9573 0.0260
-13.000 -0.6291 0.03693 0.03252 -0.1312 0.9497 0.0265
-12.750 -0.6057 0.03506 0.03052 -0.1344 0.9398 0.0269
-12.500 -0.5918 0.03348 0.02878 -0.1355 0.9258 0.0275
-12.250 -0.5865 0.03173 0.02679 -0.1347 0.9116 0.0278
-12.000 -0.5826 0.03028 0.02511 -0.1331 0.8988 0.0283
-11.500 -0.5751 0.02787 0.02224 -0.1286 0.8766 0.0292
-11.250 -0.5728 0.02708 0.02122 -0.1256 0.8672 0.0296
-11.000 -0.5618 0.02562 0.01956 -0.1239 0.8591 0.0302
-10.750 -0.5348 0.02420 0.01807 -0.1245 0.8537 0.0309
-10.500 -0.5166 0.02335 0.01716 -0.1236 0.8468 0.0313
-10.250 -0.4982 0.02266 0.01640 -0.1227 0.8399 0.0319
-10.000 -0.4784 0.02199 0.01563 -0.1219 0.8337 0.0325
-9.750 -0.4602 0.02140 0.01497 -0.1209 0.8269 0.0333
-9.500 -0.4395 0.02074 0.01418 -0.1201 0.8211 0.0340
-9.250 -0.4187 0.02017 0.01349 -0.1194 0.8157 0.0345
-9.000 -0.3990 0.01970 0.01292 -0.1184 0.8096 0.0349
-8.750 -0.3702 0.01845 0.01166 -0.1188 0.8049 0.0358
-8.500 -0.3493 0.01786 0.01105 -0.1181 0.7998 0.0366
-8.250 -0.3303 0.01735 0.01054 -0.1170 0.7940 0.0374
-8.000 -0.3107 0.01692 0.01006 -0.1161 0.7885 0.0383
-7.750 -0.2904 0.01649 0.00954 -0.1152 0.7836 0.0391
-7.500 -0.2712 0.01603 0.00907 -0.1142 0.7785 0.0399
-7.250 -0.2510 0.01564 0.00862 -0.1133 0.7735 0.0405
-7.000 -0.2327 0.01508 0.00800 -0.1122 0.7689 0.0414
-6.750 -0.2150 0.01451 0.00741 -0.1110 0.7644 0.0426
-6.500 -0.1944 0.01411 0.00701 -0.1103 0.7595 0.0439
-6.250 -0.1721 0.01378 0.00664 -0.1097 0.7550 0.0456
-6.000 -0.1486 0.01348 0.00626 -0.1093 0.7508 0.0471
-5.750 -0.1268 0.01305 0.00581 -0.1088 0.7466 0.0489
-5.500 -0.1035 0.01269 0.00545 -0.1084 0.7424 0.0516
-5.250 -0.0785 0.01242 0.00515 -0.1083 0.7385 0.0549
-5.000 -0.0537 0.01208 0.00480 -0.1082 0.7349 0.0615
-4.750 -0.0291 0.01168 0.00447 -0.1081 0.7313 0.0810
-4.500 -0.0098 0.01048 0.00392 -0.1080 0.7273 0.2239
-4.250 0.0113 0.00896 0.00333 -0.1087 0.7233 0.4562
-4.000 0.0396 0.00878 0.00333 -0.1091 0.7199 0.5321
-3.750 0.0691 0.00883 0.00335 -0.1096 0.7166 0.5601
-3.500 0.0979 0.00887 0.00339 -0.1099 0.7135 0.5768
-3.250 0.1266 0.00890 0.00342 -0.1102 0.7101 0.5885
-3.000 0.1559 0.00897 0.00342 -0.1105 0.7068 0.5998
-2.750 0.1851 0.00911 0.00353 -0.1108 0.7037 0.6152
-2.500 0.2139 0.00932 0.00374 -0.1109 0.7007 0.6305
-2.250 0.2420 0.00951 0.00397 -0.1109 0.6977 0.6426
-2.000 0.2708 0.00964 0.00406 -0.1112 0.6946 0.6505
-1.750 0.2994 0.00961 0.00402 -0.1115 0.6916 0.6538
-1.500 0.3283 0.00961 0.00401 -0.1118 0.6887 0.6564
-1.250 0.3576 0.00964 0.00400 -0.1123 0.6861 0.6592
-1.000 0.3875 0.00970 0.00401 -0.1129 0.6834 0.6622
-0.750 0.4164 0.00974 0.00402 -0.1133 0.6806 0.6651
-0.500 0.4454 0.00976 0.00402 -0.1138 0.6777 0.6679
-0.250 0.4741 0.00974 0.00401 -0.1142 0.6749 0.6706
0.000 0.5029 0.00976 0.00403 -0.1145 0.6723 0.6731
0.250 0.5321 0.00979 0.00406 -0.1150 0.6699 0.6756
0.500 0.5617 0.00986 0.00410 -0.1156 0.6674 0.6784
0.750 0.5910 0.00995 0.00418 -0.1161 0.6648 0.6815
1.000 0.6193 0.00999 0.00423 -0.1164 0.6622 0.6846
1.250 0.6480 0.01003 0.00428 -0.1168 0.6596 0.6873
1.500 0.6765 0.01005 0.00434 -0.1172 0.6570 0.6899
1.750 0.7053 0.01009 0.00440 -0.1176 0.6545 0.6926
2.000 0.7345 0.01016 0.00447 -0.1181 0.6521 0.6957
2.250 0.7645 0.01030 0.00459 -0.1187 0.6497 0.6991
2.500 0.7925 0.01038 0.00471 -0.1190 0.6473 0.7025
2.750 0.8203 0.01043 0.00480 -0.1193 0.6446 0.7055
3.000 0.8480 0.01047 0.00491 -0.1195 0.6418 0.7085
3.250 0.8764 0.01053 0.00501 -0.1198 0.6391 0.7116
3.500 0.9053 0.01058 0.00508 -0.1202 0.6360 0.7150
3.750 0.9352 0.01073 0.00520 -0.1209 0.6326 0.7188
4.000 0.9610 0.01076 0.00531 -0.1207 0.6289 0.7225
4.250 0.9875 0.01077 0.00541 -0.1206 0.6250 0.7261
4.500 1.0151 0.01080 0.00547 -0.1208 0.6210 0.7296
4.750 1.0442 0.01088 0.00553 -0.1212 0.6160 0.7335
5.000 1.0669 0.01083 0.00558 -0.1203 0.6090 0.7378
5.250 1.0930 0.01079 0.00552 -0.1201 0.6014 0.7417
5.500 1.1148 0.01076 0.00560 -0.1190 0.5927 0.7456
5.750 1.1380 0.01077 0.00559 -0.1182 0.5826 0.7502
6.000 1.1590 0.01078 0.00569 -0.1170 0.5724 0.7552
6.250 1.1804 0.01084 0.00578 -0.1159 0.5617 0.7599
6.500 1.2005 0.01094 0.00590 -0.1145 0.5505 0.7643
6.750 1.2193 0.01105 0.00607 -0.1130 0.5373 0.7695
7.000 1.2363 0.01123 0.00625 -0.1111 0.5215 0.7750
7.250 1.2462 0.01144 0.00647 -0.1078 0.5013 0.7802
7.500 1.2504 0.01185 0.00682 -0.1036 0.4735 0.7864
7.750 1.2469 0.01262 0.00743 -0.0982 0.4336 0.7936
8.000 1.2353 0.01377 0.00839 -0.0919 0.3888 0.8006
8.250 1.2221 0.01527 0.00966 -0.0859 0.3441 0.8088
8.500 1.2103 0.01689 0.01111 -0.0805 0.3010 0.8163
8.750 1.1996 0.01871 0.01273 -0.0758 0.2586 0.8251
9.000 1.1893 0.02064 0.01448 -0.0714 0.2185 0.8333
9.250 1.1818 0.02263 0.01629 -0.0678 0.1800 0.8428
9.500 1.1741 0.02466 0.01817 -0.0643 0.1442 0.8522
9.750 1.1668 0.02684 0.02018 -0.0611 0.1081 0.8630
10.000 1.1601 0.02905 0.02224 -0.0581 0.0771 0.8748
10.250 1.1566 0.03107 0.02417 -0.0555 0.0549 0.8880
10.500 1.1576 0.03275 0.02585 -0.0532 0.0451 0.9042
10.750 1.1600 0.03420 0.02735 -0.0509 0.0401 0.9274
11.000 1.1653 0.03582 0.02903 -0.0497 0.0365 1.0000
11.250 1.1770 0.03735 0.03059 -0.0493 0.0339 1.0000
11.500 1.1840 0.03925 0.03250 -0.0486 0.0318 1.0000
11.750 1.1928 0.04101 0.03430 -0.0480 0.0301 1.0000
12.000 1.2021 0.04276 0.03609 -0.0475 0.0287 1.0000
12.250 1.2100 0.04464 0.03800 -0.0469 0.0275 1.0000
12.500 1.2117 0.04714 0.04053 -0.0461 0.0265 1.0000
12.750 1.2210 0.04895 0.04241 -0.0457 0.0257 1.0000
13.000 1.2294 0.05089 0.04440 -0.0453 0.0248 1.0000
13.250 1.2372 0.05291 0.04646 -0.0450 0.0242 1.0000
13.500 1.2439 0.05506 0.04865 -0.0446 0.0235 1.0000
13.750 1.2486 0.05744 0.05107 -0.0442 0.0228 1.0000
14.000 1.2492 0.06026 0.05392 -0.0437 0.0223 1.0000
14.250 1.2587 0.06223 0.05596 -0.0436 0.0218 1.0000
14.500 1.2677 0.06425 0.05806 -0.0435 0.0213 1.0000
14.750 1.2755 0.06644 0.06032 -0.0435 0.0208 1.0000
15.000 1.2832 0.06864 0.06257 -0.0434 0.0203 1.0000
15.250 1.2908 0.07088 0.06486 -0.0435 0.0199 1.0000
15.500 1.2979 0.07320 0.06722 -0.0435 0.0196 1.0000
15.750 1.3051 0.07548 0.06953 -0.0436 0.0192 1.0000
16.000 1.3124 0.07765 0.07171 -0.0434 0.0188 1.0000
16.250 1.3215 0.07961 0.07372 -0.0432 0.0185 1.0000
16.500 1.3291 0.08198 0.07620 -0.0434 0.0183 1.0000
16.750 1.3371 0.08429 0.07859 -0.0436 0.0181 1.0000
17.000 1.3450 0.08663 0.08103 -0.0439 0.0178 1.0000
17.250 1.3523 0.08904 0.08354 -0.0442 0.0176 1.0000
17.500 1.3593 0.09150 0.08608 -0.0445 0.0174 1.0000
17.750 1.3661 0.09398 0.08866 -0.0449 0.0172 1.0000
18.000 1.3724 0.09656 0.09133 -0.0454 0.0170 1.0000
18.250 1.3780 0.09927 0.09414 -0.0460 0.0168 1.0000
18.500 1.3825 0.10214 0.09710 -0.0467 0.0166 1.0000
18.750 1.3858 0.10521 0.10026 -0.0476 0.0164 1.0000
19.000 1.3890 0.10831 0.10345 -0.0486 0.0162 1.0000
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