NACA 66(3)-418 (naca663418-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66(3)-418 (naca663418-il) Reynolds number: 500,000 Max Cl/Cd: 91.5 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca663418-il-500000.txt Download as CSV file: xf-naca663418-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-418
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5637 0.05622 0.05243 -0.1387 0.9043 0.0270
-14.250 -0.5736 0.05334 0.04940 -0.1381 0.8971 0.0271
-14.000 -0.5773 0.05110 0.04708 -0.1374 0.8909 0.0273
-13.750 -0.5985 0.04790 0.04367 -0.1354 0.8839 0.0273
-13.500 -0.6185 0.04420 0.03961 -0.1328 0.8778 0.0259
-13.250 -0.6311 0.04165 0.03687 -0.1303 0.8721 0.0259
-13.000 -0.6424 0.03925 0.03424 -0.1274 0.8665 0.0259
-12.750 -0.6496 0.03712 0.03186 -0.1246 0.8617 0.0259
-12.500 -0.6517 0.03500 0.02952 -0.1222 0.8573 0.0258
-12.250 -0.6556 0.03340 0.02768 -0.1190 0.8526 0.0261
-12.000 -0.6504 0.03178 0.02585 -0.1169 0.8486 0.0262
-11.750 -0.6468 0.03056 0.02440 -0.1143 0.8449 0.0263
-11.500 -0.6442 0.02973 0.02337 -0.1113 0.8410 0.0265
-11.250 -0.6087 0.02701 0.02056 -0.1136 0.8392 0.0273
-11.000 -0.5881 0.02598 0.01945 -0.1132 0.8362 0.0276
-10.750 -0.5668 0.02509 0.01850 -0.1128 0.8333 0.0281
-10.500 -0.5432 0.02418 0.01750 -0.1127 0.8308 0.0285
-10.250 -0.5192 0.02336 0.01657 -0.1126 0.8285 0.0290
-10.000 -0.4937 0.02259 0.01570 -0.1127 0.8262 0.0294
-9.750 -0.4692 0.02187 0.01492 -0.1126 0.8241 0.0300
-9.500 -0.4460 0.02125 0.01424 -0.1123 0.8218 0.0305
-9.250 -0.4238 0.02072 0.01363 -0.1118 0.8194 0.0310
-9.000 -0.3971 0.01993 0.01281 -0.1119 0.8174 0.0319
-8.750 -0.3751 0.01929 0.01218 -0.1115 0.8153 0.0327
-8.500 -0.3551 0.01879 0.01167 -0.1107 0.8132 0.0335
-8.250 -0.3355 0.01831 0.01116 -0.1099 0.8112 0.0342
-8.000 -0.3164 0.01790 0.01069 -0.1090 0.8091 0.0351
-7.750 -0.2986 0.01745 0.01023 -0.1078 0.8073 0.0359
-7.500 -0.2804 0.01706 0.00981 -0.1067 0.8053 0.0367
-7.250 -0.2676 0.01640 0.00915 -0.1048 0.8031 0.0378
-7.000 -0.2526 0.01591 0.00868 -0.1033 0.8011 0.0394
-6.750 -0.2352 0.01554 0.00830 -0.1020 0.7991 0.0412
-6.500 -0.2173 0.01520 0.00791 -0.1007 0.7972 0.0428
-6.250 -0.2037 0.01468 0.00738 -0.0988 0.7954 0.0449
-6.000 -0.1878 0.01431 0.00700 -0.0972 0.7936 0.0476
-5.750 -0.1708 0.01410 0.00675 -0.0957 0.7919 0.0506
-5.500 -0.1602 0.01376 0.00646 -0.0931 0.7904 0.0558
-5.250 -0.1500 0.01351 0.00626 -0.0903 0.7886 0.0642
-5.000 -0.1423 0.01307 0.00600 -0.0871 0.7867 0.0965
-4.750 -0.1439 0.01219 0.00564 -0.0826 0.7846 0.2083
-4.500 -0.1438 0.01122 0.00525 -0.0785 0.7827 0.3404
-4.250 -0.1415 0.01011 0.00478 -0.0747 0.7810 0.4916
-4.000 -0.1281 0.00960 0.00488 -0.0723 0.7797 0.6445
-3.750 -0.1006 0.00974 0.00499 -0.0724 0.7787 0.6736
-3.500 -0.0724 0.00991 0.00512 -0.0726 0.7777 0.6897
-3.250 -0.0438 0.01014 0.00532 -0.0728 0.7766 0.7013
-3.000 -0.0156 0.01047 0.00564 -0.0728 0.7754 0.7121
-2.750 0.0109 0.01086 0.00605 -0.0724 0.7744 0.7251
-2.500 0.0376 0.01140 0.00663 -0.0719 0.7733 0.7375
-2.250 0.0648 0.01189 0.00719 -0.0713 0.7722 0.7449
-2.000 0.0917 0.01232 0.00765 -0.0710 0.7710 0.7520
-1.750 0.1180 0.01245 0.00773 -0.0711 0.7697 0.7567
-1.500 0.1446 0.01255 0.00784 -0.0710 0.7686 0.7587
-1.250 0.1716 0.01267 0.00797 -0.0710 0.7673 0.7606
-1.000 0.1991 0.01277 0.00807 -0.0711 0.7661 0.7627
-0.750 0.2265 0.01286 0.00814 -0.0713 0.7650 0.7649
-0.500 0.2540 0.01291 0.00818 -0.0716 0.7640 0.7668
-0.250 0.2820 0.01292 0.00817 -0.0721 0.7630 0.7688
0.000 0.3109 0.01290 0.00812 -0.0727 0.7619 0.7708
0.250 0.3406 0.01288 0.00806 -0.0736 0.7607 0.7725
0.500 0.3707 0.01291 0.00805 -0.0745 0.7595 0.7736
0.750 0.3952 0.01294 0.00811 -0.0743 0.7579 0.7749
1.000 0.4183 0.01299 0.00821 -0.0738 0.7558 0.7759
1.250 0.4432 0.01304 0.00828 -0.0736 0.7536 0.7768
1.500 0.4697 0.01304 0.00830 -0.0737 0.7514 0.7777
1.750 0.4980 0.01299 0.00827 -0.0741 0.7494 0.7786
2.000 0.5274 0.01294 0.00823 -0.0748 0.7477 0.7797
2.250 0.5576 0.01289 0.00818 -0.0755 0.7462 0.7809
2.500 0.5889 0.01282 0.00811 -0.0765 0.7447 0.7819
2.750 0.6219 0.01278 0.00807 -0.0778 0.7430 0.7829
3.000 0.6426 0.01281 0.00817 -0.0768 0.7393 0.7842
3.250 0.6680 0.01274 0.00814 -0.0766 0.7356 0.7855
3.500 0.6987 0.01254 0.00795 -0.0774 0.7324 0.7867
3.750 0.7336 0.01223 0.00763 -0.0789 0.7293 0.7877
4.000 0.7682 0.01201 0.00739 -0.0804 0.7257 0.7888
4.250 0.7888 0.01187 0.00732 -0.0792 0.7195 0.7901
4.500 0.8218 0.01150 0.00693 -0.0802 0.7139 0.7911
4.750 0.8469 0.01113 0.00660 -0.0797 0.7053 0.7925
5.000 0.8741 0.01064 0.00607 -0.0793 0.6930 0.7938
5.250 0.8920 0.01045 0.00595 -0.0773 0.6819 0.7952
5.500 0.9110 0.01037 0.00593 -0.0757 0.6719 0.7966
5.750 0.9278 0.01028 0.00587 -0.0735 0.6581 0.7982
6.000 0.9379 0.01025 0.00587 -0.0701 0.6392 0.8001
6.250 0.9386 0.01028 0.00584 -0.0647 0.6069 0.8024
6.500 0.9252 0.01088 0.00614 -0.0570 0.5550 0.8052
6.750 0.9077 0.01196 0.00693 -0.0492 0.5037 0.8079
7.000 0.8945 0.01310 0.00786 -0.0427 0.4589 0.8105
7.250 0.8824 0.01439 0.00895 -0.0367 0.4125 0.8130
7.500 0.8722 0.01580 0.01014 -0.0313 0.3643 0.8157
7.750 0.8645 0.01727 0.01135 -0.0266 0.3142 0.8186
8.000 0.8601 0.01870 0.01253 -0.0226 0.2636 0.8216
8.250 0.8566 0.02021 0.01373 -0.0190 0.2081 0.8245
8.500 0.8552 0.02167 0.01487 -0.0157 0.1517 0.8271
8.750 0.8529 0.02323 0.01610 -0.0125 0.0942 0.8297
9.000 0.8567 0.02455 0.01721 -0.0100 0.0597 0.8324
9.250 0.8671 0.02556 0.01815 -0.0084 0.0471 0.8351
9.500 0.8796 0.02646 0.01904 -0.0070 0.0408 0.8380
9.750 0.8915 0.02745 0.02002 -0.0057 0.0369 0.8409
10.000 0.9053 0.02832 0.02093 -0.0046 0.0340 0.8437
10.250 0.9149 0.02943 0.02207 -0.0031 0.0317 0.8466
10.500 0.9283 0.03032 0.02303 -0.0019 0.0301 0.8497
10.750 0.9406 0.03132 0.02406 -0.0008 0.0285 0.8532
11.000 0.9476 0.03275 0.02550 0.0008 0.0269 0.8568
11.250 0.9615 0.03370 0.02653 0.0016 0.0260 0.8603
11.500 0.9731 0.03476 0.02766 0.0028 0.0250 0.8639
11.750 0.9845 0.03587 0.02882 0.0038 0.0241 0.8678
12.000 0.9946 0.03714 0.03014 0.0049 0.0236 0.8721
12.250 1.0014 0.03872 0.03174 0.0062 0.0229 0.8763
12.500 1.0106 0.04003 0.03314 0.0075 0.0224 0.8807
12.750 1.0224 0.04119 0.03439 0.0084 0.0220 0.8858
13.000 1.0340 0.04244 0.03571 0.0092 0.0214 0.8913
13.250 1.0446 0.04367 0.03704 0.0102 0.0209 0.8966
13.500 1.0556 0.04492 0.03837 0.0111 0.0206 0.9028
13.750 1.0666 0.04622 0.03972 0.0119 0.0202 0.9092
14.000 1.0769 0.04750 0.04107 0.0129 0.0198 0.9166
14.250 1.0878 0.04878 0.04240 0.0137 0.0195 0.9247
14.500 1.1003 0.04996 0.04363 0.0146 0.0192 0.9340
14.750 1.1160 0.05108 0.04483 0.0153 0.0188 0.9444
15.000 1.1314 0.05265 0.04655 0.0148 0.0186 0.9603
15.250 1.1462 0.05423 0.04826 0.0142 0.0184 1.0000
15.500 1.1566 0.05610 0.05025 0.0142 0.0181 1.0000
15.750 1.1673 0.05797 0.05224 0.0142 0.0178 1.0000
16.000 1.1774 0.05994 0.05432 0.0143 0.0176 1.0000
16.250 1.1859 0.06206 0.05655 0.0144 0.0174 1.0000
16.500 1.1929 0.06438 0.05899 0.0144 0.0172 1.0000
16.750 1.1982 0.06686 0.06160 0.0145 0.0171 1.0000
17.000 1.2020 0.06951 0.06437 0.0144 0.0169 1.0000
17.250 1.2039 0.07243 0.06744 0.0143 0.0168 1.0000
17.500 1.2041 0.07562 0.07077 0.0140 0.0167 1.0000
17.750 1.2007 0.07932 0.07464 0.0136 0.0167 1.0000
18.000 1.1971 0.08304 0.07850 0.0130 0.0166 1.0000
18.250 1.1855 0.08802 0.08372 0.0121 0.0166 1.0000
18.500 1.1721 0.09339 0.08931 0.0107 0.0167 1.0000
18.750 1.1559 0.09937 0.09551 0.0087 0.0167 1.0000
19.000 1.1339 0.10652 0.10292 0.0060 0.0168 1.0000
19.250 1.0993 0.11625 0.11296 0.0016 0.0170 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66(3)-418 (naca663418-il)