NACA 65(3)-618 (naca653618-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(3)-618 (naca653618-il) Reynolds number: 200,000 Max Cl/Cd: 70.19 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca653618-il-200000-n5.txt Download as CSV file: xf-naca653618-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5379 0.07121 0.06695 -0.1013 0.9812 0.0264
-13.750 -0.5693 0.06200 0.05741 -0.1092 0.9725 0.0264
-13.500 -0.5886 0.05524 0.05031 -0.1148 0.9635 0.0266
-13.250 -0.5999 0.04982 0.04451 -0.1194 0.9543 0.0269
-13.000 -0.6057 0.04518 0.03946 -0.1230 0.9444 0.0273
-12.750 -0.6110 0.04131 0.03509 -0.1255 0.9321 0.0278
-12.500 -0.5928 0.03934 0.03302 -0.1274 0.9239 0.0283
-12.250 -0.5770 0.03790 0.03150 -0.1284 0.9136 0.0288
-12.000 -0.5643 0.03626 0.02969 -0.1289 0.9038 0.0292
-11.750 -0.5518 0.03483 0.02808 -0.1289 0.8941 0.0298
-11.500 -0.5418 0.03338 0.02643 -0.1281 0.8845 0.0304
-11.250 -0.5300 0.03194 0.02475 -0.1273 0.8757 0.0309
-11.000 -0.5192 0.03069 0.02327 -0.1260 0.8669 0.0315
-10.750 -0.5078 0.02955 0.02185 -0.1246 0.8588 0.0322
-10.500 -0.4907 0.02845 0.02061 -0.1238 0.8522 0.0329
-10.250 -0.4711 0.02755 0.01968 -0.1233 0.8453 0.0334
-10.000 -0.4510 0.02670 0.01874 -0.1227 0.8395 0.0341
-9.750 -0.4319 0.02590 0.01785 -0.1219 0.8329 0.0347
-9.500 -0.4123 0.02514 0.01699 -0.1212 0.8264 0.0354
-9.250 -0.3915 0.02442 0.01613 -0.1205 0.8213 0.0363
-9.000 -0.3727 0.02378 0.01540 -0.1195 0.8151 0.0372
-8.750 -0.3528 0.02317 0.01466 -0.1186 0.8094 0.0379
-8.500 -0.3311 0.02239 0.01388 -0.1181 0.8047 0.0386
-8.250 -0.3141 0.02179 0.01328 -0.1168 0.7991 0.0393
-8.000 -0.2986 0.02126 0.01272 -0.1154 0.7930 0.0400
-7.750 -0.2815 0.02072 0.01212 -0.1142 0.7880 0.0408
-7.500 -0.2643 0.02020 0.01154 -0.1130 0.7832 0.0419
-7.250 -0.2474 0.01975 0.01104 -0.1117 0.7777 0.0432
-7.000 -0.2299 0.01927 0.01049 -0.1105 0.7730 0.0444
-6.750 -0.2126 0.01871 0.00990 -0.1094 0.7690 0.0458
-6.500 -0.1948 0.01827 0.00944 -0.1084 0.7642 0.0473
-6.250 -0.1760 0.01786 0.00898 -0.1074 0.7591 0.0489
-6.000 -0.1553 0.01747 0.00851 -0.1066 0.7547 0.0510
-5.750 -0.1340 0.01702 0.00802 -0.1061 0.7511 0.0538
-5.500 -0.1129 0.01668 0.00766 -0.1054 0.7468 0.0581
-5.250 -0.0916 0.01630 0.00730 -0.1048 0.7425 0.0648
-5.000 -0.0692 0.01589 0.00692 -0.1044 0.7387 0.0777
-4.750 -0.0471 0.01533 0.00648 -0.1041 0.7354 0.1121
-4.500 -0.0273 0.01447 0.00602 -0.1038 0.7319 0.2020
-4.250 -0.0095 0.01334 0.00553 -0.1036 0.7274 0.3486
-4.000 0.0128 0.01275 0.00558 -0.1033 0.7235 0.4961
-3.750 0.0405 0.01276 0.00561 -0.1034 0.7202 0.5414
-3.500 0.0690 0.01286 0.00568 -0.1035 0.7175 0.5715
-3.250 0.0959 0.01315 0.00601 -0.1031 0.7144 0.6060
-3.000 0.1222 0.01350 0.00635 -0.1026 0.7108 0.6308
-2.750 0.1483 0.01372 0.00661 -0.1019 0.7073 0.6406
-2.500 0.1769 0.01372 0.00650 -0.1023 0.7041 0.6466
-2.250 0.2060 0.01370 0.00637 -0.1028 0.7013 0.6502
-2.000 0.2350 0.01371 0.00632 -0.1031 0.6988 0.6528
-1.750 0.2615 0.01374 0.00634 -0.1031 0.6954 0.6557
-1.500 0.2890 0.01377 0.00633 -0.1032 0.6922 0.6589
-1.250 0.3173 0.01378 0.00629 -0.1036 0.6893 0.6624
-1.000 0.3465 0.01377 0.00620 -0.1042 0.6865 0.6658
-0.750 0.3755 0.01377 0.00615 -0.1046 0.6839 0.6685
-0.500 0.4044 0.01381 0.00615 -0.1050 0.6815 0.6710
-0.250 0.4304 0.01388 0.00625 -0.1049 0.6782 0.6738
0.000 0.4575 0.01394 0.00631 -0.1050 0.6753 0.6766
0.250 0.4855 0.01399 0.00635 -0.1053 0.6725 0.6797
0.500 0.5143 0.01404 0.00636 -0.1058 0.6699 0.6833
0.750 0.5434 0.01408 0.00637 -0.1063 0.6675 0.6865
1.000 0.5727 0.01413 0.00641 -0.1067 0.6653 0.6889
1.250 0.5984 0.01424 0.00657 -0.1066 0.6623 0.6916
1.500 0.6245 0.01435 0.00673 -0.1066 0.6594 0.6945
1.750 0.6516 0.01445 0.00686 -0.1067 0.6565 0.6979
2.000 0.6797 0.01453 0.00694 -0.1071 0.6538 0.7017
2.250 0.7084 0.01461 0.00703 -0.1075 0.6513 0.7051
2.500 0.7370 0.01469 0.00714 -0.1078 0.6492 0.7078
2.750 0.7643 0.01482 0.00731 -0.1080 0.6469 0.7109
3.000 0.7883 0.01499 0.00758 -0.1076 0.6435 0.7143
3.250 0.8142 0.01513 0.00778 -0.1076 0.6403 0.7181
3.500 0.8417 0.01526 0.00794 -0.1079 0.6375 0.7221
3.750 0.8688 0.01536 0.00811 -0.1079 0.6349 0.7253
4.000 0.8975 0.01545 0.00825 -0.1083 0.6325 0.7288
4.250 0.9236 0.01561 0.00848 -0.1082 0.6296 0.7328
4.500 0.9456 0.01581 0.00879 -0.1075 0.6250 0.7372
4.750 0.9712 0.01592 0.00897 -0.1074 0.6207 0.7413
5.000 0.9985 0.01596 0.00907 -0.1074 0.6170 0.7446
5.250 1.0260 0.01604 0.00922 -0.1075 0.6133 0.7486
5.500 1.0446 0.01625 0.00958 -0.1061 0.6076 0.7536
6.000 1.0941 0.01629 0.00976 -0.1052 0.5953 0.7628
6.250 1.1108 0.01637 0.00996 -0.1032 0.5862 0.7676
6.500 1.1297 0.01637 0.01001 -0.1016 0.5755 0.7730
6.750 1.1450 0.01635 0.01003 -0.0993 0.5608 0.7783
7.000 1.1526 0.01642 0.01015 -0.0956 0.5440 0.7834
7.250 1.1583 0.01662 0.01038 -0.0917 0.5249 0.7901
7.500 1.1655 0.01695 0.01070 -0.0883 0.5025 0.7968
7.750 1.1703 0.01741 0.01114 -0.0845 0.4747 0.8035
8.000 1.1715 0.01814 0.01173 -0.0806 0.4383 0.8115
8.250 1.1641 0.01928 0.01268 -0.0755 0.3971 0.8187
8.500 1.1542 0.02082 0.01402 -0.0707 0.3580 0.8275
8.750 1.1428 0.02261 0.01564 -0.0661 0.3203 0.8358
9.000 1.1331 0.02459 0.01745 -0.0622 0.2833 0.8457
9.250 1.1235 0.02663 0.01936 -0.0584 0.2482 0.8556
9.500 1.1153 0.02878 0.02135 -0.0552 0.2141 0.8668
9.750 1.1095 0.03087 0.02333 -0.0523 0.1830 0.8794
10.000 1.1035 0.03299 0.02532 -0.0495 0.1521 0.8941
10.250 1.0998 0.03502 0.02724 -0.0471 0.1242 0.9128
10.500 1.0973 0.03706 0.02919 -0.0451 0.0980 0.9419
11.000 1.1018 0.04117 0.03309 -0.0429 0.0611 1.0000
11.250 1.1079 0.04320 0.03507 -0.0423 0.0506 1.0000
11.500 1.1151 0.04515 0.03701 -0.0417 0.0444 1.0000
11.750 1.1222 0.04716 0.03901 -0.0413 0.0402 1.0000
12.000 1.1306 0.04908 0.04098 -0.0409 0.0370 1.0000
12.250 1.1372 0.05121 0.04311 -0.0405 0.0347 1.0000
12.500 1.1459 0.05316 0.04515 -0.0402 0.0329 1.0000
12.750 1.1531 0.05528 0.04733 -0.0399 0.0311 1.0000
13.000 1.1579 0.05769 0.04977 -0.0396 0.0299 1.0000
13.250 1.1651 0.05989 0.05206 -0.0395 0.0289 1.0000
13.500 1.1721 0.06215 0.05440 -0.0393 0.0277 1.0000
13.750 1.1783 0.06452 0.05684 -0.0393 0.0267 1.0000
14.000 1.1836 0.06701 0.05937 -0.0393 0.0259 1.0000
14.250 1.1875 0.06970 0.06210 -0.0393 0.0252 1.0000
14.500 1.1949 0.07203 0.06453 -0.0393 0.0244 1.0000
14.750 1.2013 0.07449 0.06709 -0.0395 0.0236 1.0000
15.000 1.2074 0.07701 0.06968 -0.0397 0.0229 1.0000
15.250 1.2133 0.07957 0.07230 -0.0399 0.0224 1.0000
15.500 1.2187 0.08221 0.07499 -0.0402 0.0219 1.0000
15.750 1.2240 0.08484 0.07765 -0.0405 0.0215 1.0000
16.000 1.2307 0.08734 0.08023 -0.0407 0.0211 1.0000
16.250 1.2378 0.08983 0.08283 -0.0411 0.0207 1.0000
16.500 1.2449 0.09230 0.08542 -0.0414 0.0203 1.0000
16.750 1.2517 0.09483 0.08805 -0.0418 0.0199 1.0000
17.000 1.2581 0.09742 0.09074 -0.0423 0.0195 1.0000
17.250 1.2645 0.10002 0.09343 -0.0429 0.0192 1.0000
17.500 1.2704 0.10271 0.09621 -0.0435 0.0189 1.0000
17.750 1.2762 0.10543 0.09901 -0.0443 0.0186 1.0000
18.000 1.2818 0.10815 0.10180 -0.0451 0.0184 1.0000
18.250 1.2877 0.11079 0.10448 -0.0459 0.0181 1.0000
18.500 1.2933 0.11350 0.10725 -0.0467 0.0179 1.0000
18.750 1.2943 0.11708 0.11104 -0.0480 0.0176 1.0000
19.000 1.2943 0.12086 0.11501 -0.0495 0.0174 1.0000
19.250 1.2931 0.12489 0.11922 -0.0513 0.0171 1.0000
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Polar data table (+)
Polar graphs
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