NACA 63(3)-618 (naca633618-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(3)-618 (naca633618-il) Reynolds number: 200,000 Max Cl/Cd: 73.97 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca633618-il-200000.txt Download as CSV file: xf-naca633618-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.4860 0.10327 0.09932 -0.0697 1.0000 0.0495
-14.500 -0.5245 0.09132 0.08732 -0.0759 1.0000 0.0486
-14.250 -0.6090 0.07409 0.06983 -0.0869 1.0000 0.0463
-13.750 -0.7617 0.05403 0.04882 -0.0962 1.0000 0.0439
-13.500 -0.7664 0.05174 0.04651 -0.0954 1.0000 0.0444
-13.250 -0.7697 0.05003 0.04481 -0.0939 1.0000 0.0449
-13.000 -0.7804 0.04897 0.04378 -0.0911 1.0000 0.0455
-12.750 -0.8302 0.04783 0.04252 -0.0845 0.9990 0.0449
-12.500 -0.8049 0.04559 0.04020 -0.0886 0.9933 0.0464
-12.250 -0.7926 0.04260 0.03690 -0.0927 0.9840 0.0478
-12.000 -0.7825 0.03955 0.03339 -0.0962 0.9728 0.0491
-11.750 -0.7543 0.03660 0.03024 -0.0996 0.9687 0.0508
-11.500 -0.7262 0.03507 0.02868 -0.1014 0.9615 0.0525
-11.250 -0.6946 0.03328 0.02669 -0.1044 0.9567 0.0548
-11.000 -0.6650 0.03132 0.02440 -0.1072 0.9517 0.0573
-10.750 -0.6338 0.02993 0.02309 -0.1086 0.9451 0.0595
-10.500 -0.6001 0.02864 0.02167 -0.1110 0.9399 0.0624
-10.250 -0.5749 0.02765 0.02041 -0.1119 0.9316 0.0647
-10.000 -0.5413 0.02613 0.01901 -0.1132 0.9259 0.0677
-9.750 -0.5093 0.02516 0.01796 -0.1148 0.9203 0.0709
-9.500 -0.4897 0.02452 0.01716 -0.1139 0.9095 0.0733
-9.250 -0.4604 0.02334 0.01602 -0.1145 0.9035 0.0765
-9.000 -0.4414 0.02276 0.01545 -0.1135 0.8936 0.0794
-8.750 -0.4177 0.02211 0.01468 -0.1131 0.8861 0.0828
-8.500 -0.3996 0.02137 0.01396 -0.1119 0.8771 0.0860
-8.250 -0.3794 0.02072 0.01332 -0.1111 0.8694 0.0902
-8.000 -0.3600 0.02023 0.01275 -0.1101 0.8615 0.0946
-7.750 -0.3430 0.01946 0.01203 -0.1089 0.8532 0.0998
-7.500 -0.3211 0.01892 0.01142 -0.1084 0.8471 0.1074
-7.250 -0.3053 0.01822 0.01081 -0.1073 0.8383 0.1171
-7.000 -0.2847 0.01745 0.01008 -0.1068 0.8320 0.1343
-6.750 -0.2665 0.01657 0.00938 -0.1063 0.8247 0.1669
-6.500 -0.2477 0.01543 0.00863 -0.1063 0.8174 0.2348
-6.250 -0.2241 0.01446 0.00809 -0.1067 0.8121 0.3306
-6.000 -0.1994 0.01422 0.00807 -0.1067 0.8051 0.3954
-5.750 -0.1718 0.01417 0.00804 -0.1067 0.7987 0.4337
-5.500 -0.1423 0.01420 0.00798 -0.1068 0.7938 0.4602
-5.250 -0.1155 0.01433 0.00810 -0.1066 0.7872 0.4802
-5.000 -0.0876 0.01444 0.00816 -0.1065 0.7810 0.4974
-4.750 -0.0581 0.01456 0.00817 -0.1065 0.7762 0.5135
-4.500 -0.0305 0.01477 0.00832 -0.1064 0.7701 0.5290
-4.250 -0.0037 0.01500 0.00858 -0.1058 0.7638 0.5420
-4.000 0.0248 0.01517 0.00871 -0.1055 0.7590 0.5534
-3.750 0.0538 0.01531 0.00873 -0.1057 0.7540 0.5654
-3.500 0.0793 0.01548 0.00897 -0.1049 0.7473 0.5726
-3.250 0.1092 0.01551 0.00885 -0.1053 0.7422 0.5830
-3.000 0.1372 0.01569 0.00903 -0.1047 0.7382 0.5903
-2.750 0.1636 0.01583 0.00915 -0.1046 0.7317 0.6003
-2.500 0.1909 0.01585 0.00917 -0.1042 0.7262 0.6059
-2.250 0.2201 0.01588 0.00912 -0.1043 0.7219 0.6116
-2.000 0.2489 0.01589 0.00905 -0.1048 0.7164 0.6193
-1.750 0.2753 0.01592 0.00910 -0.1044 0.7107 0.6240
-1.500 0.3037 0.01595 0.00911 -0.1044 0.7061 0.6292
-1.250 0.3350 0.01595 0.00898 -0.1051 0.7024 0.6362
-1.000 0.3607 0.01599 0.00906 -0.1049 0.6960 0.6416
-0.750 0.3878 0.01603 0.00911 -0.1046 0.6908 0.6462
-0.500 0.4179 0.01603 0.00904 -0.1050 0.6867 0.6522
-0.250 0.4478 0.01607 0.00901 -0.1058 0.6824 0.6587
0.000 0.4727 0.01617 0.00919 -0.1052 0.6766 0.6629
0.250 0.5009 0.01619 0.00921 -0.1053 0.6719 0.6680
0.500 0.5326 0.01619 0.00910 -0.1061 0.6680 0.6746
0.750 0.5589 0.01630 0.00926 -0.1060 0.6630 0.6796
1.000 0.5847 0.01642 0.00943 -0.1057 0.6578 0.6844
1.250 0.6141 0.01645 0.00944 -0.1061 0.6534 0.6902
1.500 0.6461 0.01646 0.00936 -0.1070 0.6498 0.6966
1.750 0.6697 0.01665 0.00966 -0.1062 0.6444 0.7012
2.000 0.6963 0.01677 0.00983 -0.1061 0.6393 0.7072
2.250 0.7276 0.01680 0.00980 -0.1070 0.6351 0.7142
2.500 0.7569 0.01686 0.00985 -0.1071 0.6316 0.7186
2.750 0.7796 0.01708 0.01020 -0.1064 0.6258 0.7244
3.000 0.8088 0.01718 0.01031 -0.1070 0.6207 0.7322
3.250 0.8364 0.01721 0.01036 -0.1068 0.6167 0.7370
3.500 0.8645 0.01736 0.01053 -0.1068 0.6125 0.7433
3.750 0.8899 0.01757 0.01082 -0.1069 0.6066 0.7507
4.000 0.9155 0.01764 0.01096 -0.1063 0.6019 0.7559
4.250 0.9457 0.01769 0.01099 -0.1067 0.5980 0.7631
4.500 0.9707 0.01792 0.01132 -0.1065 0.5927 0.7703
4.750 0.9938 0.01808 0.01158 -0.1057 0.5871 0.7764
5.000 1.0240 0.01812 0.01161 -0.1062 0.5825 0.7844
5.250 1.0513 0.01822 0.01175 -0.1060 0.5779 0.7908
5.500 1.0720 0.01841 0.01209 -0.1049 0.5711 0.7986
5.750 1.1007 0.01837 0.01205 -0.1050 0.5654 0.8063
6.000 1.1256 0.01842 0.01216 -0.1044 0.5592 0.8136
6.250 1.1486 0.01849 0.01233 -0.1037 0.5516 0.8224
6.500 1.1767 0.01838 0.01220 -0.1034 0.5459 0.8301
6.750 1.1964 0.01855 0.01252 -0.1022 0.5379 0.8394
7.000 1.2202 0.01845 0.01246 -0.1012 0.5308 0.8479
7.250 1.2416 0.01852 0.01261 -0.1001 0.5232 0.8576
7.500 1.2623 0.01850 0.01267 -0.0987 0.5150 0.8679
7.750 1.2816 0.01849 0.01272 -0.0971 0.5069 0.8782
8.000 1.2996 0.01836 0.01264 -0.0952 0.4962 0.8900
8.250 1.3111 0.01833 0.01272 -0.0922 0.4844 0.9041
8.500 1.3230 0.01822 0.01264 -0.0892 0.4730 0.9205
8.750 1.3313 0.01813 0.01261 -0.0856 0.4619 0.9434
9.000 1.3462 0.01820 0.01281 -0.0839 0.4493 1.0000
9.250 1.3663 0.01854 0.01318 -0.0835 0.4352 1.0000
9.500 1.3830 0.01900 0.01365 -0.0825 0.4201 1.0000
9.750 1.3956 0.01959 0.01424 -0.0810 0.4036 1.0000
10.000 1.4045 0.02034 0.01498 -0.0790 0.3851 1.0000
10.250 1.4095 0.02132 0.01590 -0.0767 0.3645 1.0000
10.500 1.4113 0.02256 0.01707 -0.0741 0.3420 1.0000
10.750 1.4095 0.02412 0.01853 -0.0715 0.3176 1.0000
11.000 1.4051 0.02602 0.02031 -0.0689 0.2938 1.0000
11.250 1.3991 0.02819 0.02237 -0.0664 0.2692 1.0000
11.500 1.3917 0.03065 0.02471 -0.0642 0.2459 1.0000
11.750 1.3839 0.03332 0.02727 -0.0623 0.2227 1.0000
12.000 1.3743 0.03629 0.03013 -0.0606 0.2022 1.0000
12.250 1.3669 0.03928 0.03304 -0.0592 0.1816 1.0000
12.500 1.3587 0.04249 0.03617 -0.0581 0.1626 1.0000
12.750 1.3502 0.04591 0.03950 -0.0572 0.1455 1.0000
13.000 1.3417 0.04950 0.04300 -0.0566 0.1299 1.0000
13.250 1.3340 0.05316 0.04658 -0.0561 0.1162 1.0000
13.500 1.3282 0.05675 0.05012 -0.0558 0.1044 1.0000
13.750 1.3250 0.06016 0.05351 -0.0557 0.0947 1.0000
14.000 1.3225 0.06356 0.05690 -0.0557 0.0873 1.0000
14.250 1.3197 0.06705 0.06034 -0.0557 0.0816 1.0000
14.500 1.3226 0.06994 0.06329 -0.0559 0.0763 1.0000
14.750 1.3231 0.07313 0.06644 -0.0561 0.0722 1.0000
15.000 1.3270 0.07593 0.06929 -0.0562 0.0684 1.0000
15.250 1.3309 0.07882 0.07221 -0.0566 0.0650 1.0000
15.500 1.3350 0.08150 0.07481 -0.0567 0.0621 1.0000
15.750 1.3411 0.08418 0.07763 -0.0571 0.0595 1.0000
16.000 1.3466 0.08690 0.08039 -0.0575 0.0570 1.0000
16.250 1.3545 0.08905 0.08245 -0.0575 0.0546 1.0000
16.500 1.3607 0.09175 0.08528 -0.0580 0.0527 1.0000
16.750 1.3668 0.09444 0.08806 -0.0585 0.0506 1.0000
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Polar data table (+)
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