NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)-615 (naca632615-il) Reynolds number: 100,000 Max Cl/Cd: 55.01 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca632615-il-100000.txt Download as CSV file: xf-naca632615-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-615
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3340 0.10499 0.10009 -0.0477 1.0000 0.1568
-10.000 -0.3954 0.10382 0.09920 -0.0498 1.0000 0.1629
-9.750 -0.3821 0.10038 0.09580 -0.0463 1.0000 0.1651
-9.500 -0.3717 0.09900 0.09442 -0.0421 1.0000 0.1684
-9.250 -0.3850 0.09812 0.09364 -0.0386 1.0000 0.1720
-9.000 -0.4161 0.09717 0.09283 -0.0359 1.0000 0.1762
-8.750 -0.5005 0.09677 0.09270 -0.0353 1.0000 0.1789
-8.500 -0.4564 0.09381 0.08968 -0.0308 1.0000 0.1829
-8.250 -0.6037 0.05726 0.05213 -0.0684 0.9769 0.0916
-8.000 -0.5860 0.05026 0.04451 -0.0733 0.9706 0.0839
-7.750 -0.5717 0.04495 0.03859 -0.0755 0.9622 0.0811
-7.500 -0.5397 0.04131 0.03444 -0.0791 0.9570 0.0829
-7.250 -0.5164 0.03856 0.03122 -0.0802 0.9495 0.0843
-7.000 -0.4819 0.03574 0.02785 -0.0827 0.9440 0.0858
-6.750 -0.4473 0.03386 0.02541 -0.0849 0.9384 0.0893
-6.500 -0.4200 0.03184 0.02339 -0.0857 0.9316 0.0930
-6.250 -0.3805 0.03042 0.02178 -0.0881 0.9270 0.0982
-6.000 -0.3507 0.02928 0.02040 -0.0887 0.9205 0.1034
-5.750 -0.3200 0.02805 0.01929 -0.0896 0.9141 0.1096
-5.500 -0.2790 0.02692 0.01808 -0.0921 0.9101 0.1191
-5.250 -0.2558 0.02624 0.01750 -0.0916 0.9023 0.1280
-5.000 -0.2225 0.02531 0.01669 -0.0929 0.8964 0.1438
-4.750 -0.1803 0.02396 0.01562 -0.0961 0.8929 0.1804
-4.500 -0.1592 0.02185 0.01507 -0.0972 0.8850 0.4005
-4.250 -0.1251 0.02226 0.01569 -0.0976 0.8790 0.5250
-4.000 -0.0826 0.02283 0.01618 -0.0989 0.8757 0.5709
-3.750 -0.0722 0.02351 0.01684 -0.0955 0.8651 0.5931
-3.500 -0.0383 0.02415 0.01747 -0.0949 0.8607 0.6199
-3.250 -0.0188 0.02480 0.01806 -0.0927 0.8528 0.6427
-3.000 0.0024 0.02545 0.01872 -0.0900 0.8460 0.6618
-2.750 0.0346 0.02587 0.01911 -0.0888 0.8425 0.6807
-2.500 0.0429 0.02644 0.01963 -0.0855 0.8322 0.6953
-2.250 0.0739 0.02659 0.01971 -0.0850 0.8276 0.7115
-2.000 0.1074 0.02663 0.01969 -0.0843 0.8248 0.7238
-1.750 0.1099 0.02716 0.02020 -0.0806 0.8132 0.7333
-1.500 0.1496 0.02691 0.01982 -0.0826 0.8098 0.7456
-1.250 0.1569 0.02737 0.02030 -0.0791 0.8003 0.7537
-1.000 0.1883 0.02728 0.02011 -0.0799 0.7952 0.7643
-0.750 0.2246 0.02702 0.01978 -0.0807 0.7922 0.7736
-0.500 0.2301 0.02763 0.02039 -0.0780 0.7815 0.7827
-0.250 0.2651 0.02743 0.02012 -0.0791 0.7774 0.7927
0.000 0.3010 0.02710 0.01974 -0.0797 0.7748 0.8010
0.250 0.3053 0.02796 0.02060 -0.0776 0.7634 0.8115
0.500 0.3365 0.02767 0.02029 -0.0773 0.7599 0.8198
0.750 0.3755 0.02734 0.01991 -0.0789 0.7573 0.8295
1.000 0.3715 0.02840 0.02102 -0.0751 0.7453 0.8398
1.250 0.4069 0.02801 0.02060 -0.0757 0.7425 0.8492
1.500 0.4064 0.02913 0.02176 -0.0728 0.7315 0.8610
1.750 0.4356 0.02891 0.02153 -0.0725 0.7276 0.8716
2.000 0.4716 0.02838 0.02100 -0.0729 0.7252 0.8822
2.250 0.4608 0.02983 0.02251 -0.0686 0.7128 0.8967
2.500 0.4961 0.02935 0.02203 -0.0691 0.7099 0.9095
2.750 0.5344 0.02874 0.02142 -0.0698 0.7079 0.9230
3.000 0.5211 0.03033 0.02310 -0.0656 0.6948 0.9449
3.250 0.5702 0.02964 0.02244 -0.0683 0.6927 0.9608
3.500 0.5885 0.03127 0.02418 -0.0703 0.6806 1.0000
3.750 0.6393 0.03076 0.02368 -0.0739 0.6778 1.0000
4.000 0.6929 0.03001 0.02294 -0.0776 0.6759 1.0000
4.750 0.8032 0.03049 0.02356 -0.0842 0.6584 1.0000
5.000 0.8109 0.03242 0.02555 -0.0839 0.6455 1.0000
5.250 0.8287 0.03371 0.02692 -0.0843 0.6354 1.0000
5.500 0.8752 0.03292 0.02619 -0.0864 0.6305 1.0000
5.750 0.9353 0.03113 0.02447 -0.0893 0.6280 1.0000
6.000 0.9475 0.03242 0.02585 -0.0885 0.6158 1.0000
6.250 1.0090 0.03031 0.02382 -0.0914 0.6122 1.0000
6.500 1.0290 0.03087 0.02447 -0.0907 0.6007 1.0000
6.750 1.0925 0.02842 0.02207 -0.0936 0.5951 1.0000
7.000 1.1174 0.02834 0.02210 -0.0930 0.5824 1.0000
7.250 1.1536 0.02745 0.02127 -0.0933 0.5705 1.0000
7.500 1.1932 0.02610 0.01997 -0.0937 0.5562 1.0000
7.750 1.2250 0.02503 0.01892 -0.0931 0.5378 1.0000
8.000 1.2528 0.02424 0.01815 -0.0921 0.5182 1.0000
8.250 1.2792 0.02367 0.01759 -0.0911 0.4980 1.0000
8.500 1.2933 0.02374 0.01776 -0.0887 0.4760 1.0000
8.750 1.3075 0.02377 0.01782 -0.0863 0.4509 1.0000
9.000 1.3138 0.02415 0.01823 -0.0829 0.4214 1.0000
9.250 1.3140 0.02476 0.01876 -0.0787 0.3877 1.0000
9.500 1.3084 0.02591 0.01976 -0.0743 0.3448 1.0000
9.750 1.2965 0.02776 0.02126 -0.0698 0.2958 1.0000
10.000 1.2798 0.03038 0.02350 -0.0658 0.2479 1.0000
10.250 1.2625 0.03352 0.02627 -0.0624 0.2061 1.0000
10.500 1.2475 0.03687 0.02927 -0.0596 0.1737 1.0000
10.750 1.2385 0.04001 0.03217 -0.0575 0.1484 1.0000
11.000 1.2352 0.04282 0.03477 -0.0558 0.1307 1.0000
11.250 1.2384 0.04520 0.03701 -0.0544 0.1171 1.0000
11.500 1.2471 0.04724 0.03898 -0.0532 0.1061 1.0000
11.750 1.2599 0.04909 0.04075 -0.0521 0.0972 1.0000
12.000 1.2810 0.05057 0.04198 -0.0513 0.0888 1.0000
12.250 1.2918 0.05258 0.04423 -0.0505 0.0833 1.0000
12.500 1.3221 0.05397 0.04539 -0.0501 0.0766 1.0000
12.750 1.3323 0.05615 0.04786 -0.0493 0.0727 1.0000
13.000 1.3518 0.05804 0.04979 -0.0488 0.0688 1.0000
13.250 1.3840 0.06031 0.05209 -0.0486 0.0650 1.0000
13.500 1.3887 0.06312 0.05521 -0.0477 0.0628 1.0000
13.750 1.3970 0.06584 0.05813 -0.0471 0.0606 1.0000
14.000 1.4068 0.06862 0.06105 -0.0467 0.0587 1.0000
14.250 1.4322 0.07201 0.06450 -0.0467 0.0569 1.0000
14.500 1.4301 0.07642 0.06920 -0.0461 0.0563 1.0000
14.750 1.4168 0.08071 0.07384 -0.0456 0.0561 1.0000
15.000 1.4010 0.08540 0.07885 -0.0454 0.0559 1.0000
15.250 1.3830 0.09050 0.08426 -0.0458 0.0558 1.0000
15.500 1.3632 0.09600 0.09006 -0.0467 0.0558 1.0000
15.750 1.3420 0.10194 0.09628 -0.0482 0.0559 1.0000
16.000 1.3196 0.10836 0.10296 -0.0504 0.0560 1.0000
16.250 1.2975 0.11523 0.11007 -0.0533 0.0561 1.0000
16.500 1.2751 0.12262 0.11767 -0.0568 0.0563 1.0000
16.750 1.1006 0.16359 0.15938 -0.0867 0.0646 1.0000
17.000 1.0895 0.17333 0.16911 -0.0920 0.0658 1.0000
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Polar data table (+)
Polar graphs
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