NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 642-015 AIRFOIL (n64015-il) Reynolds number: 50,000 Max Cl/Cd: 27.05 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64015-il-50000-n5.txt Download as CSV file: xf-n64015-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 642-015 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7502 0.10087 0.09324 -0.0223 1.0000 0.0574
-13.250 -0.7786 0.09252 0.08476 -0.0273 1.0000 0.0571
-13.000 -0.8031 0.08564 0.07772 -0.0309 1.0000 0.0568
-12.750 -0.8279 0.07946 0.07134 -0.0337 1.0000 0.0566
-12.500 -0.8491 0.07424 0.06591 -0.0354 1.0000 0.0567
-12.250 -0.8673 0.06970 0.06113 -0.0362 1.0000 0.0568
-12.000 -0.8831 0.06568 0.05682 -0.0364 1.0000 0.0572
-11.750 -0.8966 0.06209 0.05292 -0.0358 1.0000 0.0577
-11.500 -0.9071 0.05893 0.04942 -0.0346 1.0000 0.0584
-11.250 -0.8955 0.05634 0.04680 -0.0343 1.0000 0.0600
-11.000 -0.8875 0.05392 0.04424 -0.0336 1.0000 0.0614
-10.750 -0.8778 0.05146 0.04158 -0.0328 1.0000 0.0630
-10.500 -0.8633 0.04900 0.03887 -0.0322 1.0000 0.0646
-10.250 -0.8464 0.04671 0.03626 -0.0317 1.0000 0.0671
-10.000 -0.8228 0.04464 0.03398 -0.0316 1.0000 0.0704
-9.750 -0.7945 0.04300 0.03234 -0.0317 1.0000 0.0743
-9.500 -0.7611 0.04155 0.03067 -0.0317 1.0000 0.0790
-9.250 -0.7318 0.04032 0.02944 -0.0314 1.0000 0.0850
-9.000 -0.7067 0.03921 0.02824 -0.0307 1.0000 0.0914
-8.750 -0.6869 0.03800 0.02706 -0.0297 1.0000 0.0981
-8.500 -0.6714 0.03675 0.02577 -0.0287 1.0000 0.1073
-8.250 -0.6611 0.03530 0.02446 -0.0274 1.0000 0.1162
-8.000 -0.6536 0.03379 0.02304 -0.0260 1.0000 0.1280
-7.750 -0.6501 0.03222 0.02163 -0.0242 1.0000 0.1436
-7.500 -0.6511 0.03064 0.02026 -0.0217 1.0000 0.1638
-7.250 -0.6576 0.02911 0.01905 -0.0184 1.0000 0.1905
-7.000 -0.6676 0.02769 0.01800 -0.0143 1.0000 0.2279
-6.750 -0.6834 0.02655 0.01732 -0.0088 1.0000 0.2731
-6.500 -0.6977 0.02580 0.01718 -0.0028 1.0000 0.3405
-6.250 -0.7003 0.02597 0.01792 0.0028 1.0000 0.4308
-6.000 -0.6752 0.02629 0.01816 0.0029 0.9867 0.5054
-5.750 -0.6415 0.02717 0.01889 0.0026 0.9748 0.5529
-5.500 -0.6056 0.02837 0.01992 0.0025 0.9645 0.5881
-5.250 -0.5597 0.03017 0.02156 0.0023 0.9577 0.6151
-5.000 -0.5180 0.03112 0.02229 0.0013 0.9496 0.6355
-4.750 -0.4769 0.03171 0.02266 0.0001 0.9413 0.6487
-4.500 -0.4386 0.03172 0.02246 -0.0017 0.9331 0.6602
-4.250 -0.4156 0.03127 0.02182 -0.0020 0.9210 0.6721
-4.000 -0.3747 0.03142 0.02178 -0.0037 0.9131 0.6774
-3.750 -0.3481 0.03101 0.02120 -0.0044 0.9031 0.6862
-3.500 -0.3209 0.03081 0.02087 -0.0046 0.8929 0.6924
-3.250 -0.2887 0.03060 0.02050 -0.0057 0.8849 0.6988
-3.000 -0.2723 0.03019 0.01998 -0.0047 0.8737 0.7069
-2.750 -0.2423 0.03011 0.01980 -0.0051 0.8655 0.7121
-2.500 -0.2268 0.02964 0.01921 -0.0040 0.8558 0.7210
-2.250 -0.1995 0.02960 0.01910 -0.0040 0.8473 0.7255
-2.000 -0.1737 0.02942 0.01884 -0.0040 0.8397 0.7313
-1.750 -0.1600 0.02909 0.01843 -0.0026 0.8303 0.7391
-1.500 -0.1308 0.02902 0.01830 -0.0029 0.8235 0.7434
-1.250 -0.1111 0.02889 0.01812 -0.0021 0.8154 0.7499
-1.000 -0.0915 0.02867 0.01786 -0.0015 0.8080 0.7565
-0.750 -0.0643 0.02865 0.01780 -0.0016 0.8018 0.7613
-0.500 -0.0471 0.02855 0.01768 -0.0006 0.7936 0.7689
-0.250 -0.0195 0.02845 0.01755 -0.0007 0.7885 0.7745
0.000 0.0000 0.02856 0.01769 0.0000 0.7805 0.7805
0.250 0.0195 0.02845 0.01755 0.0007 0.7745 0.7885
0.500 0.0471 0.02855 0.01768 0.0006 0.7689 0.7936
0.750 0.0643 0.02865 0.01780 0.0016 0.7613 0.8018
1.000 0.0915 0.02867 0.01785 0.0015 0.7565 0.8081
1.250 0.1111 0.02888 0.01812 0.0021 0.7499 0.8155
1.500 0.1308 0.02902 0.01830 0.0029 0.7434 0.8235
1.750 0.1600 0.02908 0.01842 0.0026 0.7391 0.8304
2.000 0.1737 0.02942 0.01884 0.0040 0.7313 0.8397
2.250 0.1995 0.02960 0.01910 0.0040 0.7256 0.8474
2.500 0.2269 0.02964 0.01921 0.0040 0.7211 0.8558
2.750 0.2423 0.03011 0.01980 0.0051 0.7122 0.8655
3.000 0.2722 0.03018 0.01998 0.0047 0.7069 0.8737
3.250 0.2888 0.03060 0.02050 0.0056 0.6988 0.8850
3.500 0.3209 0.03081 0.02086 0.0046 0.6924 0.8929
3.750 0.3483 0.03100 0.02119 0.0044 0.6862 0.9031
4.000 0.3748 0.03141 0.02177 0.0037 0.6774 0.9131
4.250 0.4157 0.03126 0.02181 0.0020 0.6721 0.9210
4.500 0.4388 0.03172 0.02245 0.0017 0.6602 0.9331
4.750 0.4771 0.03169 0.02265 -0.0002 0.6487 0.9414
5.000 0.5183 0.03111 0.02228 -0.0014 0.6355 0.9497
5.250 0.5598 0.03017 0.02155 -0.0023 0.6151 0.9578
5.500 0.6056 0.02836 0.01991 -0.0025 0.5881 0.9646
5.750 0.6416 0.02716 0.01888 -0.0026 0.5527 0.9749
6.000 0.6753 0.02628 0.01815 -0.0030 0.5054 0.9867
6.500 0.6976 0.02579 0.01718 0.0028 0.3410 1.0000
6.750 0.6833 0.02654 0.01731 0.0088 0.2731 1.0000
7.000 0.6678 0.02768 0.01799 0.0142 0.2280 1.0000
7.250 0.6578 0.02911 0.01904 0.0183 0.1902 1.0000
7.500 0.6513 0.03064 0.02026 0.0217 0.1635 1.0000
7.750 0.6504 0.03222 0.02163 0.0241 0.1434 1.0000
8.000 0.6539 0.03380 0.02304 0.0259 0.1276 1.0000
8.250 0.6617 0.03530 0.02445 0.0274 0.1161 1.0000
8.500 0.6720 0.03676 0.02577 0.0286 0.1069 1.0000
8.750 0.6876 0.03800 0.02705 0.0296 0.0980 1.0000
9.000 0.7075 0.03921 0.02824 0.0306 0.0913 1.0000
9.250 0.7321 0.04034 0.02945 0.0313 0.0847 1.0000
9.500 0.7623 0.04155 0.03068 0.0316 0.0789 1.0000
9.750 0.7953 0.04302 0.03235 0.0316 0.0741 1.0000
10.000 0.8238 0.04466 0.03398 0.0314 0.0702 1.0000
10.250 0.8473 0.04675 0.03631 0.0315 0.0670 1.0000
10.500 0.8642 0.04902 0.03889 0.0321 0.0645 1.0000
10.750 0.8788 0.05150 0.04162 0.0327 0.0629 1.0000
11.000 0.8885 0.05394 0.04426 0.0335 0.0613 1.0000
11.250 0.8970 0.05635 0.04679 0.0341 0.0598 1.0000
11.500 0.9075 0.05899 0.04945 0.0345 0.0583 1.0000
11.750 0.8970 0.06218 0.05299 0.0356 0.0577 1.0000
12.000 0.8847 0.06570 0.05684 0.0362 0.0572 1.0000
12.250 0.8676 0.06978 0.06122 0.0360 0.0567 1.0000
12.500 0.8502 0.07429 0.06597 0.0352 0.0566 1.0000
12.750 0.8288 0.07959 0.07147 0.0334 0.0567 1.0000
13.000 0.8045 0.08571 0.07779 0.0307 0.0568 1.0000
13.250 0.7778 0.09289 0.08513 0.0268 0.0570 1.0000
13.500 0.7522 0.10088 0.09325 0.0221 0.0575 1.0000
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