NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(2)-415 (naca642415-il) Reynolds number: 100,000 Max Cl/Cd: 51.25 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca642415-il-100000-n5.txt Download as CSV file: xf-naca642415-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(2)-415
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4993 0.09576 0.09027 -0.0545 1.0000 0.0389
-12.250 -0.5417 0.08169 0.07617 -0.0636 1.0000 0.0382
-12.000 -0.5809 0.07206 0.06641 -0.0701 1.0000 0.0376
-11.750 -0.6131 0.06534 0.05954 -0.0739 1.0000 0.0373
-11.500 -0.6398 0.06034 0.05438 -0.0756 1.0000 0.0371
-11.250 -0.6637 0.05640 0.05028 -0.0757 1.0000 0.0371
-11.000 -0.6855 0.05344 0.04717 -0.0741 1.0000 0.0371
-10.750 -0.7085 0.05134 0.04497 -0.0706 1.0000 0.0371
-10.500 -0.7288 0.04951 0.04303 -0.0664 1.0000 0.0372
-10.250 -0.7479 0.04793 0.04132 -0.0618 1.0000 0.0374
-10.000 -0.7431 0.04485 0.03787 -0.0621 0.9926 0.0379
-9.750 -0.7248 0.04152 0.03404 -0.0644 0.9829 0.0391
-9.500 -0.7038 0.03856 0.03049 -0.0662 0.9739 0.0404
-9.250 -0.6769 0.03656 0.02841 -0.0678 0.9665 0.0416
-9.000 -0.6460 0.03462 0.02627 -0.0700 0.9609 0.0427
-8.750 -0.6178 0.03285 0.02429 -0.0712 0.9533 0.0439
-8.500 -0.5864 0.03118 0.02238 -0.0728 0.9472 0.0458
-8.250 -0.5573 0.02979 0.02067 -0.0737 0.9397 0.0478
-8.000 -0.5271 0.02839 0.01932 -0.0749 0.9329 0.0497
-7.750 -0.4963 0.02721 0.01809 -0.0760 0.9266 0.0517
-7.500 -0.4693 0.02620 0.01697 -0.0763 0.9180 0.0540
-7.250 -0.4381 0.02518 0.01583 -0.0773 0.9121 0.0573
-7.000 -0.4162 0.02433 0.01503 -0.0769 0.9020 0.0601
-6.750 -0.3881 0.02347 0.01410 -0.0774 0.8956 0.0636
-6.500 -0.3673 0.02279 0.01336 -0.0765 0.8853 0.0677
-6.250 -0.3419 0.02201 0.01258 -0.0767 0.8785 0.0733
-6.000 -0.3214 0.02140 0.01191 -0.0758 0.8686 0.0793
-5.750 -0.2966 0.02067 0.01115 -0.0758 0.8619 0.0894
-5.500 -0.2769 0.02002 0.01055 -0.0749 0.8521 0.1034
-5.250 -0.2532 0.01917 0.00983 -0.0748 0.8456 0.1324
-5.000 -0.2351 0.01819 0.00919 -0.0742 0.8362 0.1978
-4.750 -0.2167 0.01676 0.00860 -0.0738 0.8293 0.3550
-4.500 -0.1952 0.01654 0.00879 -0.0727 0.8211 0.4745
-4.250 -0.1687 0.01657 0.00878 -0.0722 0.8143 0.5233
-4.000 -0.1424 0.01669 0.00886 -0.0716 0.8076 0.5570
-3.750 -0.1175 0.01692 0.00908 -0.0705 0.8002 0.5826
-3.500 -0.0905 0.01717 0.00924 -0.0697 0.7948 0.6090
-3.250 -0.0673 0.01756 0.00965 -0.0681 0.7871 0.6298
-3.000 -0.0412 0.01771 0.00972 -0.0672 0.7808 0.6446
-2.750 -0.0138 0.01770 0.00960 -0.0669 0.7750 0.6520
-2.500 0.0128 0.01762 0.00940 -0.0670 0.7677 0.6594
-2.250 0.0404 0.01759 0.00930 -0.0667 0.7625 0.6643
-2.000 0.0674 0.01757 0.00918 -0.0667 0.7565 0.6708
-1.750 0.0946 0.01751 0.00903 -0.0668 0.7501 0.6770
-1.500 0.1226 0.01747 0.00892 -0.0666 0.7451 0.6815
-1.250 0.1491 0.01746 0.00886 -0.0666 0.7387 0.6870
-1.000 0.1771 0.01740 0.00872 -0.0670 0.7327 0.6932
-0.750 0.2051 0.01737 0.00864 -0.0668 0.7282 0.6972
-0.500 0.2312 0.01743 0.00868 -0.0666 0.7224 0.7025
-0.250 0.2589 0.01744 0.00865 -0.0669 0.7168 0.7091
0.000 0.2867 0.01744 0.00862 -0.0669 0.7125 0.7137
0.250 0.3134 0.01749 0.00867 -0.0667 0.7074 0.7188
0.500 0.3401 0.01756 0.00873 -0.0668 0.7014 0.7253
0.750 0.3675 0.01759 0.00876 -0.0667 0.6969 0.7308
1.000 0.3954 0.01763 0.00879 -0.0667 0.6932 0.7367
1.250 0.4210 0.01780 0.00900 -0.0668 0.6873 0.7443
1.500 0.4465 0.01791 0.00916 -0.0663 0.6826 0.7494
1.750 0.4745 0.01796 0.00922 -0.0663 0.6788 0.7560
2.000 0.5006 0.01811 0.00941 -0.0663 0.6739 0.7630
2.250 0.5245 0.01830 0.00970 -0.0657 0.6687 0.7696
2.500 0.5523 0.01842 0.00984 -0.0659 0.6646 0.7780
2.750 0.5793 0.01848 0.00995 -0.0655 0.6612 0.7845
3.000 0.6025 0.01876 0.01034 -0.0651 0.6553 0.7930
3.250 0.6269 0.01892 0.01059 -0.0645 0.6501 0.8002
3.500 0.6548 0.01897 0.01069 -0.0644 0.6458 0.8088
3.750 0.6780 0.01918 0.01102 -0.0637 0.6403 0.8172
4.000 0.7017 0.01941 0.01136 -0.0631 0.6345 0.8271
4.250 0.7272 0.01948 0.01151 -0.0625 0.6301 0.8357
4.500 0.7517 0.01966 0.01181 -0.0620 0.6249 0.8460
4.750 0.7722 0.01988 0.01218 -0.0608 0.6180 0.8565
5.000 0.7995 0.01974 0.01211 -0.0602 0.6121 0.8668
5.250 0.8179 0.01987 0.01241 -0.0585 0.6019 0.8794
5.750 0.8661 0.01936 0.01202 -0.0560 0.5793 0.9067
6.000 0.8858 0.01921 0.01198 -0.0542 0.5644 0.9240
6.250 0.9092 0.01903 0.01193 -0.0532 0.5481 0.9444
6.750 0.9604 0.01891 0.01193 -0.0529 0.4995 1.0000
7.000 0.9793 0.01911 0.01213 -0.0517 0.4672 1.0000
7.250 0.9954 0.01947 0.01244 -0.0502 0.4216 1.0000
7.500 1.0045 0.02016 0.01267 -0.0475 0.3488 1.0000
7.750 1.0032 0.02146 0.01351 -0.0439 0.2828 1.0000
8.000 0.9997 0.02307 0.01475 -0.0404 0.2288 1.0000
8.250 0.9979 0.02480 0.01619 -0.0375 0.1840 1.0000
8.500 0.9984 0.02655 0.01770 -0.0352 0.1474 1.0000
8.750 1.0009 0.02829 0.01927 -0.0334 0.1203 1.0000
9.000 1.0048 0.03002 0.02087 -0.0317 0.1012 1.0000
9.250 1.0101 0.03174 0.02251 -0.0303 0.0876 1.0000
9.500 1.0168 0.03341 0.02418 -0.0291 0.0777 1.0000
9.750 1.0232 0.03516 0.02591 -0.0280 0.0705 1.0000
10.000 1.0302 0.03690 0.02765 -0.0270 0.0648 1.0000
10.250 1.0379 0.03864 0.02942 -0.0260 0.0602 1.0000
10.500 1.0460 0.04037 0.03120 -0.0252 0.0563 1.0000
10.750 1.0527 0.04226 0.03309 -0.0244 0.0533 1.0000
11.000 1.0628 0.04393 0.03486 -0.0237 0.0500 1.0000
11.250 1.0719 0.04569 0.03666 -0.0230 0.0476 1.0000
11.500 1.0798 0.04761 0.03855 -0.0224 0.0455 1.0000
11.750 1.0921 0.04924 0.04033 -0.0218 0.0432 1.0000
12.000 1.1030 0.05099 0.04216 -0.0212 0.0411 1.0000
12.250 1.1139 0.05278 0.04399 -0.0208 0.0396 1.0000
12.500 1.1265 0.05455 0.04572 -0.0202 0.0384 1.0000
12.750 1.1403 0.05634 0.04770 -0.0197 0.0370 1.0000
13.000 1.1519 0.05833 0.04986 -0.0193 0.0356 1.0000
13.250 1.1618 0.06044 0.05211 -0.0190 0.0344 1.0000
13.500 1.1709 0.06262 0.05438 -0.0188 0.0334 1.0000
13.750 1.1804 0.06479 0.05659 -0.0187 0.0324 1.0000
14.000 1.1901 0.06727 0.05918 -0.0184 0.0318 1.0000
14.250 1.1940 0.07035 0.06256 -0.0184 0.0312 1.0000
14.500 1.1951 0.07379 0.06627 -0.0185 0.0307 1.0000
14.750 1.1932 0.07757 0.07033 -0.0189 0.0303 1.0000
15.000 1.1882 0.08178 0.07480 -0.0196 0.0300 1.0000
15.250 1.1804 0.08641 0.07969 -0.0208 0.0297 1.0000
15.500 1.1696 0.09158 0.08513 -0.0224 0.0295 1.0000
15.750 1.1558 0.09735 0.09117 -0.0246 0.0294 1.0000
16.000 1.1388 0.10388 0.09797 -0.0275 0.0293 1.0000
16.250 1.1184 0.11140 0.10574 -0.0314 0.0293 1.0000
16.500 1.0927 0.12041 0.11503 -0.0366 0.0294 1.0000
16.750 1.0590 0.13210 0.12700 -0.0441 0.0296 1.0000
17.000 1.0030 0.15177 0.14695 -0.0573 0.0304 1.0000
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