NACA 65(4)-421 (naca654421-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(4)-421 (naca654421-il) Reynolds number: 200,000 Max Cl/Cd: 56.95 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca654421-il-200000-n5.txt Download as CSV file: xf-naca654421-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(4)-421
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.6200 0.11792 0.11347 -0.0704 1.0000 0.0299
-18.250 -0.6900 0.10066 0.09582 -0.0805 1.0000 0.0297
-18.000 -0.7221 0.09190 0.08681 -0.0852 1.0000 0.0297
-17.750 -0.7453 0.08518 0.07987 -0.0885 1.0000 0.0298
-17.500 -0.7629 0.07963 0.07412 -0.0909 1.0000 0.0299
-17.250 -0.7778 0.07481 0.06910 -0.0927 1.0000 0.0301
-17.000 -0.7900 0.07053 0.06462 -0.0940 1.0000 0.0302
-16.750 -0.7992 0.06682 0.06073 -0.0949 1.0000 0.0304
-16.500 -0.8070 0.06345 0.05717 -0.0954 1.0000 0.0306
-16.250 -0.8133 0.06042 0.05396 -0.0957 1.0000 0.0309
-16.000 -0.8199 0.05756 0.05088 -0.0957 1.0000 0.0311
-15.750 -0.8190 0.05541 0.04862 -0.0955 1.0000 0.0314
-15.500 -0.8105 0.05388 0.04708 -0.0950 1.0000 0.0317
-15.250 -0.7881 0.05175 0.04489 -0.0975 0.9751 0.0320
-15.000 -0.7659 0.04982 0.04286 -0.1003 0.9605 0.0324
-14.750 -0.7424 0.04794 0.04085 -0.1030 0.9485 0.0329
-14.500 -0.7183 0.04621 0.03898 -0.1055 0.9374 0.0332
-14.250 -0.6946 0.04462 0.03725 -0.1077 0.9261 0.0337
-14.000 -0.6730 0.04325 0.03574 -0.1091 0.9138 0.0342
-13.750 -0.6536 0.04197 0.03432 -0.1100 0.9022 0.0348
-13.500 -0.6341 0.04083 0.03303 -0.1106 0.8913 0.0353
-13.250 -0.6164 0.03979 0.03185 -0.1107 0.8806 0.0358
-13.000 -0.5967 0.03888 0.03085 -0.1108 0.8716 0.0363
-12.750 -0.5792 0.03804 0.03000 -0.1105 0.8625 0.0367
-12.500 -0.5627 0.03717 0.02908 -0.1101 0.8545 0.0371
-12.250 -0.5479 0.03629 0.02817 -0.1096 0.8463 0.0377
-12.000 -0.5333 0.03542 0.02723 -0.1090 0.8384 0.0382
-11.750 -0.5191 0.03456 0.02630 -0.1084 0.8311 0.0387
-11.500 -0.5059 0.03369 0.02537 -0.1076 0.8234 0.0393
-11.250 -0.4931 0.03281 0.02441 -0.1068 0.8168 0.0401
-11.000 -0.4804 0.03195 0.02348 -0.1060 0.8101 0.0407
-10.750 -0.4676 0.03111 0.02256 -0.1051 0.8037 0.0414
-10.500 -0.4579 0.03012 0.02153 -0.1040 0.7980 0.0421
-10.250 -0.4472 0.02920 0.02058 -0.1030 0.7921 0.0429
-10.000 -0.4362 0.02831 0.01965 -0.1020 0.7858 0.0442
-9.750 -0.4245 0.02748 0.01875 -0.1009 0.7803 0.0456
-9.500 -0.4128 0.02668 0.01786 -0.0998 0.7751 0.0470
-9.250 -0.4026 0.02580 0.01697 -0.0986 0.7693 0.0484
-9.000 -0.3918 0.02497 0.01611 -0.0974 0.7642 0.0503
-8.750 -0.3800 0.02422 0.01527 -0.0961 0.7599 0.0526
-8.500 -0.3687 0.02346 0.01450 -0.0948 0.7552 0.0555
-8.250 -0.3579 0.02270 0.01373 -0.0935 0.7501 0.0600
-8.000 -0.3480 0.02191 0.01296 -0.0919 0.7455 0.0668
-7.750 -0.3391 0.02110 0.01215 -0.0902 0.7414 0.0790
-7.500 -0.3337 0.02018 0.01134 -0.0880 0.7369 0.0995
-7.250 -0.3314 0.01920 0.01052 -0.0855 0.7320 0.1300
-7.000 -0.3319 0.01820 0.00969 -0.0823 0.7276 0.1649
-6.750 -0.3369 0.01738 0.00899 -0.0782 0.7239 0.1994
-6.250 -0.3407 0.01571 0.00778 -0.0706 0.7162 0.3011
-6.000 -0.3390 0.01478 0.00725 -0.0672 0.7121 0.3803
-5.750 -0.3259 0.01434 0.00722 -0.0652 0.7086 0.4633
-5.500 -0.3023 0.01430 0.00720 -0.0646 0.7056 0.5030
-5.250 -0.2769 0.01439 0.00727 -0.0642 0.7028 0.5312
-5.000 -0.2527 0.01452 0.00738 -0.0637 0.6994 0.5542
-4.750 -0.2269 0.01474 0.00758 -0.0634 0.6961 0.5710
-4.500 -0.1996 0.01505 0.00790 -0.0631 0.6931 0.5839
-4.250 -0.1725 0.01531 0.00811 -0.0629 0.6904 0.5959
-4.000 -0.1445 0.01554 0.00828 -0.0628 0.6879 0.6043
-3.750 -0.1177 0.01544 0.00801 -0.0631 0.6855 0.6102
-3.500 -0.0901 0.01547 0.00803 -0.0631 0.6826 0.6126
-3.250 -0.0630 0.01549 0.00804 -0.0632 0.6794 0.6151
-3.000 -0.0358 0.01548 0.00798 -0.0633 0.6764 0.6177
-2.750 -0.0084 0.01544 0.00788 -0.0635 0.6738 0.6205
-2.500 0.0193 0.01537 0.00774 -0.0638 0.6715 0.6236
-2.250 0.0473 0.01528 0.00754 -0.0643 0.6694 0.6265
-2.000 0.0760 0.01522 0.00737 -0.0649 0.6674 0.6292
-1.750 0.1031 0.01524 0.00740 -0.0649 0.6649 0.6311
-1.500 0.1296 0.01527 0.00744 -0.0650 0.6620 0.6330
-1.250 0.1566 0.01528 0.00745 -0.0651 0.6591 0.6350
-1.000 0.1841 0.01528 0.00742 -0.0653 0.6565 0.6373
-0.750 0.2120 0.01528 0.00739 -0.0656 0.6543 0.6399
-0.500 0.2404 0.01527 0.00733 -0.0661 0.6523 0.6428
-0.250 0.2694 0.01526 0.00725 -0.0667 0.6505 0.6456
0.000 0.2987 0.01526 0.00719 -0.0673 0.6488 0.6479
0.250 0.3238 0.01534 0.00733 -0.0671 0.6461 0.6496
0.500 0.3496 0.01541 0.00745 -0.0671 0.6432 0.6515
0.750 0.3761 0.01548 0.00755 -0.0671 0.6406 0.6538
1.000 0.4034 0.01554 0.00763 -0.0673 0.6383 0.6564
1.250 0.4313 0.01560 0.00768 -0.0677 0.6363 0.6591
1.500 0.4599 0.01564 0.00771 -0.0681 0.6344 0.6618
1.750 0.4893 0.01568 0.00771 -0.0688 0.6327 0.6646
2.000 0.5184 0.01574 0.00776 -0.0694 0.6308 0.6669
2.250 0.5412 0.01589 0.00802 -0.0688 0.6278 0.6689
2.500 0.5657 0.01604 0.00825 -0.0686 0.6252 0.6711
2.750 0.5912 0.01618 0.00845 -0.0685 0.6228 0.6738
3.000 0.6177 0.01629 0.00861 -0.0686 0.6204 0.6767
3.250 0.6455 0.01638 0.00872 -0.0689 0.6182 0.6798
3.500 0.6745 0.01644 0.00879 -0.0694 0.6162 0.6828
3.750 0.7043 0.01653 0.00887 -0.0702 0.6145 0.6857
4.000 0.7298 0.01668 0.00912 -0.0701 0.6123 0.6879
4.250 0.7493 0.01694 0.00951 -0.0690 0.6089 0.6904
4.500 0.7717 0.01714 0.00980 -0.0684 0.6058 0.6932
4.750 0.7968 0.01728 0.01001 -0.0682 0.6028 0.6964
5.000 0.8247 0.01734 0.01011 -0.0685 0.6000 0.7000
5.250 0.8554 0.01736 0.01014 -0.0693 0.5975 0.7037
5.500 0.8800 0.01749 0.01037 -0.0690 0.5944 0.7067
5.750 0.8940 0.01778 0.01081 -0.0670 0.5894 0.7095
6.000 0.9165 0.01785 0.01097 -0.0663 0.5848 0.7127
6.250 0.9474 0.01769 0.01083 -0.0669 0.5803 0.7161
6.500 0.9617 0.01784 0.01109 -0.0648 0.5736 0.7201
6.750 0.9803 0.01784 0.01113 -0.0634 0.5661 0.7244
7.000 1.0016 0.01775 0.01111 -0.0623 0.5591 0.7276
7.250 1.0043 0.01795 0.01144 -0.0581 0.5506 0.7318
7.500 1.0180 0.01797 0.01151 -0.0557 0.5410 0.7363
7.750 1.0291 0.01807 0.01162 -0.0531 0.5284 0.7412
8.000 1.0295 0.01860 0.01223 -0.0491 0.5144 0.7456
8.250 1.0328 0.01912 0.01281 -0.0457 0.4979 0.7499
8.500 1.0388 0.01968 0.01338 -0.0429 0.4795 0.7548
8.750 1.0412 0.02048 0.01413 -0.0398 0.4517 0.7604
9.000 1.0401 0.02146 0.01495 -0.0363 0.4149 0.7656
9.250 1.0307 0.02299 0.01627 -0.0321 0.3756 0.7711
9.500 1.0192 0.02489 0.01798 -0.0282 0.3401 0.7773
9.750 1.0084 0.02697 0.01989 -0.0248 0.3071 0.7834
10.000 0.9994 0.02904 0.02185 -0.0218 0.2784 0.7889
10.250 0.9907 0.03128 0.02397 -0.0191 0.2483 0.7951
10.500 0.9860 0.03345 0.02602 -0.0170 0.2209 0.8016
10.750 0.9818 0.03560 0.02809 -0.0150 0.1961 0.8074
11.000 0.9791 0.03779 0.03018 -0.0133 0.1702 0.8145
11.250 0.9781 0.03995 0.03224 -0.0119 0.1461 0.8216
11.500 0.9766 0.04215 0.03435 -0.0105 0.1218 0.8291
12.000 0.9779 0.04649 0.03849 -0.0083 0.0794 0.8452
12.250 0.9805 0.04860 0.04053 -0.0074 0.0636 0.8541
12.750 0.9887 0.05255 0.04447 -0.0058 0.0465 0.8738
13.000 0.9943 0.05439 0.04637 -0.0051 0.0425 0.8863
13.250 0.9993 0.05632 0.04835 -0.0044 0.0399 0.9020
13.500 1.0063 0.05815 0.05029 -0.0040 0.0377 0.9240
13.750 1.0129 0.06002 0.05227 -0.0042 0.0360 0.9820
14.250 1.0266 0.06447 0.05681 -0.0045 0.0331 1.0000
14.500 1.0335 0.06679 0.05918 -0.0048 0.0317 1.0000
14.750 1.0393 0.06925 0.06168 -0.0051 0.0310 1.0000
15.000 1.0437 0.07188 0.06434 -0.0055 0.0301 1.0000
15.250 1.0505 0.07428 0.06682 -0.0058 0.0293 1.0000
15.500 1.0568 0.07676 0.06938 -0.0063 0.0286 1.0000
15.750 1.0628 0.07928 0.07195 -0.0067 0.0280 1.0000
16.000 1.0683 0.08189 0.07462 -0.0073 0.0274 1.0000
16.250 1.0738 0.08451 0.07728 -0.0078 0.0269 1.0000
16.500 1.0789 0.08716 0.07997 -0.0084 0.0265 1.0000
16.750 1.0839 0.08981 0.08263 -0.0090 0.0260 1.0000
17.000 1.0915 0.09222 0.08513 -0.0096 0.0256 1.0000
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