NACA 63(3)-618 (naca633618-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(3)-618 (naca633618-il) Reynolds number: 100,000 Max Cl/Cd: 46.46 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca633618-il-100000-n5.txt Download as CSV file: xf-naca633618-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5632 0.08488 0.07899 -0.0798 1.0000 0.0446
-14.250 -0.6130 0.07427 0.06813 -0.0864 1.0000 0.0442
-14.000 -0.6445 0.06764 0.06130 -0.0898 1.0000 0.0443
-13.750 -0.6690 0.06255 0.05602 -0.0917 1.0000 0.0445
-13.500 -0.6897 0.05839 0.05166 -0.0926 1.0000 0.0449
-13.250 -0.7091 0.05483 0.04790 -0.0927 1.0000 0.0454
-13.000 -0.7269 0.05192 0.04481 -0.0919 1.0000 0.0459
-12.750 -0.7410 0.04991 0.04272 -0.0900 1.0000 0.0465
-12.500 -0.7517 0.04884 0.04169 -0.0870 1.0000 0.0470
-12.250 -0.7399 0.04707 0.03988 -0.0884 0.9929 0.0482
-12.000 -0.7224 0.04469 0.03731 -0.0914 0.9827 0.0499
-11.750 -0.7070 0.04220 0.03452 -0.0940 0.9717 0.0517
-11.500 -0.6866 0.04020 0.03234 -0.0961 0.9622 0.0535
-11.250 -0.6586 0.03863 0.03072 -0.0987 0.9557 0.0555
-11.000 -0.6368 0.03705 0.02896 -0.1002 0.9458 0.0578
-10.750 -0.6091 0.03534 0.02700 -0.1025 0.9394 0.0603
-10.500 -0.5847 0.03420 0.02590 -0.1033 0.9297 0.0624
-10.250 -0.5559 0.03291 0.02449 -0.1051 0.9232 0.0653
-10.000 -0.5342 0.03183 0.02320 -0.1053 0.9131 0.0679
-9.750 -0.5057 0.03072 0.02214 -0.1064 0.9066 0.0705
-9.500 -0.4860 0.02986 0.02124 -0.1061 0.8967 0.0732
-9.250 -0.4615 0.02897 0.02019 -0.1064 0.8892 0.0767
-9.000 -0.4440 0.02814 0.01940 -0.1058 0.8797 0.0795
-8.750 -0.4234 0.02732 0.01854 -0.1056 0.8716 0.0830
-8.500 -0.4056 0.02666 0.01777 -0.1048 0.8628 0.0871
-8.250 -0.3892 0.02585 0.01700 -0.1041 0.8544 0.0915
-8.000 -0.3711 0.02517 0.01625 -0.1034 0.8469 0.0974
-7.750 -0.3564 0.02445 0.01555 -0.1023 0.8381 0.1035
-7.500 -0.3358 0.02371 0.01475 -0.1020 0.8321 0.1131
-7.250 -0.3212 0.02308 0.01415 -0.1008 0.8233 0.1250
-7.000 -0.3024 0.02231 0.01342 -0.1003 0.8164 0.1423
-6.750 -0.2831 0.02151 0.01271 -0.1000 0.8102 0.1677
-6.500 -0.2661 0.02076 0.01212 -0.0994 0.8023 0.2022
-6.250 -0.2448 0.01989 0.01147 -0.0994 0.7965 0.2552
-6.000 -0.2233 0.01924 0.01112 -0.0993 0.7903 0.3170
-5.750 -0.2008 0.01898 0.01109 -0.0988 0.7832 0.3741
-5.500 -0.1735 0.01888 0.01100 -0.0988 0.7779 0.4171
-5.250 -0.1461 0.01888 0.01093 -0.0988 0.7726 0.4492
-5.000 -0.1215 0.01904 0.01109 -0.0981 0.7656 0.4724
-4.750 -0.0937 0.01915 0.01113 -0.0979 0.7602 0.4930
-4.500 -0.0644 0.01926 0.01112 -0.0978 0.7560 0.5104
-4.250 -0.0403 0.01941 0.01121 -0.0973 0.7488 0.5245
-4.000 -0.0131 0.01951 0.01124 -0.0969 0.7432 0.5366
-3.750 0.0155 0.01962 0.01126 -0.0966 0.7389 0.5475
-3.500 0.0413 0.01971 0.01126 -0.0965 0.7326 0.5601
-3.250 0.0663 0.01991 0.01145 -0.0955 0.7268 0.5679
-3.000 0.0964 0.01978 0.01115 -0.0962 0.7222 0.5776
-2.750 0.1233 0.01984 0.01118 -0.0957 0.7175 0.5828
-2.500 0.1479 0.01993 0.01124 -0.0952 0.7110 0.5893
-2.250 0.1772 0.01983 0.01101 -0.0958 0.7060 0.5975
-2.000 0.2055 0.01984 0.01097 -0.0956 0.7022 0.6022
-1.750 0.2305 0.01993 0.01105 -0.0952 0.6963 0.6082
-1.500 0.2587 0.01989 0.01090 -0.0958 0.6905 0.6161
-1.250 0.2860 0.01991 0.01090 -0.0954 0.6862 0.6203
-1.000 0.3155 0.01989 0.01081 -0.0956 0.6827 0.6256
-0.750 0.3397 0.02002 0.01094 -0.0954 0.6762 0.6322
-0.500 0.3670 0.02004 0.01093 -0.0955 0.6711 0.6376
-0.250 0.3954 0.02004 0.01089 -0.0954 0.6671 0.6421
0.000 0.4231 0.02009 0.01092 -0.0955 0.6627 0.6479
0.250 0.4492 0.02023 0.01104 -0.0958 0.6569 0.6549
0.500 0.4749 0.02031 0.01115 -0.0953 0.6523 0.6590
0.750 0.5041 0.02031 0.01112 -0.0955 0.6486 0.6640
1.000 0.5311 0.02043 0.01122 -0.0957 0.6438 0.6704
1.250 0.5553 0.02062 0.01146 -0.0954 0.6381 0.6762
1.500 0.5815 0.02073 0.01160 -0.0951 0.6339 0.6812
1.750 0.6116 0.02075 0.01158 -0.0955 0.6304 0.6873
2.000 0.6378 0.02094 0.01179 -0.0957 0.6254 0.6939
2.250 0.6594 0.02119 0.01213 -0.0947 0.6198 0.6987
2.500 0.6863 0.02131 0.01228 -0.0946 0.6156 0.7051
2.750 0.7181 0.02133 0.01226 -0.0955 0.6122 0.7124
3.000 0.7387 0.02163 0.01267 -0.0944 0.6069 0.7174
3.250 0.7613 0.02190 0.01303 -0.0937 0.6014 0.7237
3.500 0.7904 0.02201 0.01314 -0.0942 0.5972 0.7313
3.750 0.8192 0.02202 0.01317 -0.0941 0.5938 0.7369
4.000 0.8374 0.02247 0.01376 -0.0929 0.5875 0.7441
4.250 0.8617 0.02271 0.01407 -0.0926 0.5822 0.7512
4.500 0.8890 0.02276 0.01416 -0.0924 0.5781 0.7577
4.750 0.9163 0.02293 0.01438 -0.0925 0.5738 0.7658
5.000 0.9319 0.02340 0.01501 -0.0908 0.5672 0.7726
5.250 0.9574 0.02355 0.01522 -0.0905 0.5624 0.7804
5.500 0.9893 0.02352 0.01521 -0.0911 0.5586 0.7883
5.750 1.0012 0.02410 0.01597 -0.0888 0.5517 0.7964
6.000 1.0245 0.02433 0.01628 -0.0883 0.5459 0.8052
6.250 1.0540 0.02422 0.01622 -0.0883 0.5415 0.8132
6.500 1.0663 0.02479 0.01695 -0.0863 0.5340 0.8231
6.750 1.0870 0.02489 0.01715 -0.0850 0.5275 0.8325
7.000 1.1138 0.02482 0.01713 -0.0846 0.5214 0.8423
7.250 1.1219 0.02532 0.01780 -0.0818 0.5125 0.8542
7.500 1.1508 0.02499 0.01749 -0.0815 0.5062 0.8650
7.750 1.1502 0.02565 0.01835 -0.0774 0.4969 0.8799
8.000 1.1742 0.02541 0.01816 -0.0763 0.4896 0.8948
8.250 1.1704 0.02602 0.01894 -0.0718 0.4804 0.9198
8.500 1.1949 0.02572 0.01870 -0.0710 0.4719 0.9573
8.750 1.2001 0.02667 0.01979 -0.0691 0.4605 1.0000
9.000 1.2183 0.02716 0.02032 -0.0685 0.4496 1.0000
9.250 1.2382 0.02751 0.02068 -0.0679 0.4379 1.0000
9.500 1.2414 0.02877 0.02204 -0.0660 0.4244 1.0000
9.750 1.2482 0.02988 0.02321 -0.0645 0.4098 1.0000
10.000 1.2537 0.03111 0.02445 -0.0629 0.3932 1.0000
10.250 1.2577 0.03251 0.02583 -0.0613 0.3745 1.0000
10.500 1.2614 0.03400 0.02727 -0.0598 0.3537 1.0000
10.750 1.2617 0.03592 0.02915 -0.0584 0.3316 1.0000
11.000 1.2627 0.03785 0.03097 -0.0570 0.3086 1.0000
11.250 1.2625 0.04001 0.03303 -0.0558 0.2866 1.0000
11.500 1.2606 0.04245 0.03539 -0.0547 0.2649 1.0000
11.750 1.2578 0.04508 0.03794 -0.0538 0.2443 1.0000
12.000 1.2543 0.04790 0.04067 -0.0530 0.2254 1.0000
12.250 1.2513 0.05084 0.04355 -0.0524 0.2075 1.0000
12.500 1.2484 0.05389 0.04655 -0.0520 0.1908 1.0000
12.750 1.2458 0.05702 0.04965 -0.0518 0.1754 1.0000
13.000 1.2432 0.06027 0.05286 -0.0517 0.1609 1.0000
13.250 1.2408 0.06360 0.05615 -0.0518 0.1477 1.0000
13.500 1.2387 0.06699 0.05952 -0.0520 0.1354 1.0000
13.750 1.2380 0.07033 0.06287 -0.0523 0.1240 1.0000
14.000 1.2372 0.07371 0.06627 -0.0526 0.1138 1.0000
14.250 1.2360 0.07724 0.06980 -0.0531 0.1049 1.0000
14.500 1.2344 0.08088 0.07343 -0.0537 0.0972 1.0000
14.750 1.2357 0.08420 0.07681 -0.0543 0.0900 1.0000
15.000 1.2349 0.08782 0.08041 -0.0550 0.0846 1.0000
15.250 1.2371 0.09109 0.08376 -0.0557 0.0790 1.0000
15.500 1.2372 0.09466 0.08730 -0.0566 0.0750 1.0000
15.750 1.2411 0.09775 0.09049 -0.0573 0.0706 1.0000
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Polar data table (+)
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