NACA 63 (naca633418-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63 (naca633418-il) Reynolds number: 100,000 Max Cl/Cd: 45.41 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca633418-il-100000.txt Download as CSV file: xf-naca633418-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6475 0.08257 0.07691 -0.0727 1.0000 0.0845
-13.500 -0.6710 0.07608 0.07033 -0.0755 1.0000 0.0838
-13.250 -0.7021 0.06992 0.06404 -0.0781 1.0000 0.0832
-13.000 -0.7311 0.06477 0.05873 -0.0795 1.0000 0.0828
-12.750 -0.7575 0.06047 0.05427 -0.0799 1.0000 0.0825
-12.500 -0.7822 0.05699 0.05062 -0.0792 1.0000 0.0825
-12.250 -0.8049 0.05422 0.04770 -0.0772 1.0000 0.0825
-12.000 -0.8294 0.05232 0.04570 -0.0734 1.0000 0.0826
-11.750 -0.8558 0.05110 0.04441 -0.0680 1.0000 0.0827
-11.500 -0.8841 0.05036 0.04360 -0.0618 1.0000 0.0827
-11.250 -0.9084 0.04943 0.04255 -0.0562 1.0000 0.0829
-11.000 -0.9268 0.04814 0.04107 -0.0515 1.0000 0.0833
-10.750 -0.9397 0.04666 0.03936 -0.0475 1.0000 0.0839
-10.500 -0.9329 0.04429 0.03657 -0.0472 0.9962 0.0851
-10.250 -0.8983 0.04141 0.03369 -0.0500 0.9910 0.0877
-10.000 -0.8641 0.03954 0.03168 -0.0529 0.9844 0.0914
-9.750 -0.8347 0.03770 0.02944 -0.0550 0.9771 0.0955
-9.500 -0.7977 0.03556 0.02732 -0.0576 0.9716 0.1000
-9.250 -0.7630 0.03418 0.02583 -0.0599 0.9652 0.1060
-9.000 -0.7286 0.03257 0.02416 -0.0618 0.9586 0.1122
-8.750 -0.6870 0.03126 0.02280 -0.0651 0.9540 0.1214
-8.500 -0.6605 0.03008 0.02176 -0.0655 0.9457 0.1299
-8.250 -0.6228 0.02878 0.02055 -0.0680 0.9403 0.1432
-8.000 -0.5946 0.02769 0.01958 -0.0690 0.9332 0.1586
-7.750 -0.5685 0.02656 0.01861 -0.0699 0.9255 0.1805
-7.500 -0.5349 0.02489 0.01734 -0.0727 0.9208 0.2218
-7.250 -0.5303 0.02379 0.01664 -0.0703 0.9093 0.2693
-7.000 -0.5020 0.02269 0.01628 -0.0719 0.9039 0.3763
-6.750 -0.4882 0.02303 0.01672 -0.0696 0.8935 0.4270
-6.500 -0.4506 0.02353 0.01712 -0.0709 0.8881 0.4701
-6.250 -0.4248 0.02434 0.01792 -0.0698 0.8804 0.4933
-6.000 -0.3951 0.02520 0.01875 -0.0690 0.8732 0.5133
-5.750 -0.3547 0.02612 0.01962 -0.0696 0.8691 0.5320
-5.500 -0.3385 0.02684 0.02028 -0.0671 0.8596 0.5460
-5.250 -0.3059 0.02751 0.02086 -0.0669 0.8538 0.5616
-5.000 -0.2651 0.02865 0.02198 -0.0666 0.8502 0.5734
-4.750 -0.2540 0.02947 0.02279 -0.0632 0.8401 0.5832
-4.500 -0.2227 0.02980 0.02300 -0.0630 0.8348 0.5974
-4.250 -0.1810 0.03096 0.02414 -0.0621 0.8316 0.6046
-4.000 -0.1792 0.03107 0.02420 -0.0591 0.8205 0.6165
-3.750 -0.1431 0.03180 0.02489 -0.0582 0.8163 0.6234
-3.500 -0.1282 0.03166 0.02466 -0.0570 0.8089 0.6349
-3.250 -0.1072 0.03221 0.02520 -0.0548 0.8015 0.6408
-3.000 -0.0788 0.03166 0.02450 -0.0558 0.7971 0.6524
-2.750 -0.0653 0.03231 0.02517 -0.0528 0.7894 0.6574
-2.500 -0.0477 0.03190 0.02464 -0.0529 0.7822 0.6689
-2.250 -0.0142 0.03194 0.02464 -0.0524 0.7787 0.6736
-2.000 -0.0075 0.03240 0.02511 -0.0496 0.7698 0.6800
-1.750 0.0132 0.03209 0.02471 -0.0499 0.7637 0.6895
-1.500 0.0455 0.03205 0.02463 -0.0496 0.7605 0.6943
-1.250 0.0500 0.03246 0.02502 -0.0475 0.7512 0.7022
-1.000 0.0727 0.03233 0.02484 -0.0473 0.7454 0.7091
-0.750 0.1045 0.03220 0.02468 -0.0472 0.7423 0.7145
-0.500 0.1079 0.03276 0.02521 -0.0459 0.7332 0.7233
-0.250 0.1286 0.03285 0.02530 -0.0448 0.7274 0.7284
0.000 0.1621 0.03261 0.02503 -0.0451 0.7243 0.7344
0.250 0.2040 0.03207 0.02438 -0.0479 0.7222 0.7430
0.500 0.1818 0.03371 0.02613 -0.0423 0.7095 0.7478
0.750 0.2169 0.03342 0.02581 -0.0430 0.7065 0.7543
1.000 0.2596 0.03290 0.02522 -0.0453 0.7045 0.7620
1.250 0.2316 0.03493 0.02736 -0.0396 0.6914 0.7677
1.500 0.2703 0.03458 0.02698 -0.0410 0.6886 0.7750
1.750 0.3117 0.03406 0.02644 -0.0424 0.6867 0.7817
2.000 0.2750 0.03654 0.02900 -0.0363 0.6729 0.7889
2.250 0.3237 0.03603 0.02845 -0.0393 0.6706 0.7967
2.500 0.3618 0.03548 0.02794 -0.0394 0.6689 0.8026
2.750 0.3238 0.03830 0.03081 -0.0341 0.6546 0.8119
3.000 0.3652 0.03772 0.03025 -0.0350 0.6524 0.8186
3.250 0.4096 0.03715 0.02971 -0.0363 0.6505 0.8260
3.500 0.3720 0.04012 0.03273 -0.0312 0.6364 0.8353
3.750 0.4139 0.03943 0.03207 -0.0319 0.6342 0.8437
4.000 0.3860 0.04227 0.03497 -0.0280 0.6213 0.8536
4.250 0.4237 0.04179 0.03452 -0.0285 0.6180 0.8628
4.500 0.4652 0.04091 0.03369 -0.0287 0.6161 0.8714
4.750 0.4377 0.04388 0.03672 -0.0253 0.6023 0.8841
5.000 0.4764 0.04311 0.03599 -0.0252 0.5996 0.8950
5.250 0.4566 0.04567 0.03862 -0.0223 0.5870 0.9091
5.500 0.4936 0.04492 0.03794 -0.0222 0.5833 0.9226
5.750 0.5303 0.04434 0.03743 -0.0223 0.5796 0.9378
6.000 0.5331 0.04639 0.03960 -0.0226 0.5670 0.9587
6.250 0.5640 0.04765 0.04098 -0.0259 0.5571 0.9881
6.500 0.6023 0.04754 0.04092 -0.0280 0.5504 1.0000
6.750 0.6615 0.04584 0.03929 -0.0304 0.5478 1.0000
7.000 0.6649 0.04837 0.04186 -0.0315 0.5338 1.0000
7.250 0.7254 0.04620 0.03978 -0.0334 0.5313 1.0000
7.500 0.7940 0.04293 0.03660 -0.0352 0.5303 1.0000
7.750 0.8747 0.03861 0.03239 -0.0375 0.5303 1.0000
8.000 0.9832 0.03305 0.02691 -0.0429 0.5293 1.0000
8.250 0.9872 0.03405 0.02800 -0.0414 0.5152 1.0000
8.500 1.0341 0.03223 0.02626 -0.0426 0.5041 1.0000
8.750 1.1154 0.02838 0.02236 -0.0467 0.4931 1.0000
9.000 1.1515 0.02736 0.02135 -0.0473 0.4786 1.0000
9.250 1.1724 0.02710 0.02115 -0.0464 0.4628 1.0000
9.500 1.1926 0.02681 0.02089 -0.0452 0.4458 1.0000
9.750 1.2083 0.02661 0.02068 -0.0433 0.4275 1.0000
10.000 1.2079 0.02725 0.02136 -0.0401 0.4081 1.0000
10.250 1.2065 0.02814 0.02226 -0.0371 0.3860 1.0000
10.500 1.2091 0.02894 0.02296 -0.0346 0.3600 1.0000
10.750 1.2043 0.03045 0.02435 -0.0320 0.3312 1.0000
11.000 1.1972 0.03238 0.02609 -0.0296 0.3000 1.0000
11.250 1.1878 0.03477 0.02823 -0.0274 0.2683 1.0000
11.500 1.1775 0.03749 0.03071 -0.0255 0.2385 1.0000
11.750 1.1681 0.04036 0.03330 -0.0239 0.2122 1.0000
12.000 1.1614 0.04321 0.03593 -0.0226 0.1893 1.0000
12.250 1.1595 0.04576 0.03820 -0.0215 0.1704 1.0000
12.500 1.1620 0.04807 0.04032 -0.0206 0.1542 1.0000
12.750 1.1687 0.05013 0.04223 -0.0199 0.1408 1.0000
13.000 1.1752 0.05228 0.04441 -0.0193 0.1300 1.0000
13.250 1.1870 0.05407 0.04615 -0.0187 0.1207 1.0000
13.500 1.2065 0.05534 0.04721 -0.0181 0.1122 1.0000
13.750 1.2144 0.05752 0.04955 -0.0177 0.1060 1.0000
14.000 1.2400 0.05861 0.05046 -0.0172 0.0994 1.0000
14.250 1.2467 0.06100 0.05307 -0.0169 0.0951 1.0000
14.500 1.2680 0.06239 0.05435 -0.0166 0.0903 1.0000
14.750 1.2849 0.06456 0.05663 -0.0163 0.0866 1.0000
15.000 1.2909 0.06725 0.05954 -0.0161 0.0838 1.0000
15.250 1.3009 0.06964 0.06204 -0.0160 0.0810 1.0000
15.500 1.3307 0.07142 0.06370 -0.0159 0.0774 1.0000
15.750 1.3199 0.07529 0.06791 -0.0159 0.0763 1.0000
16.000 1.3102 0.07944 0.07237 -0.0162 0.0752 1.0000
16.250 1.2996 0.08389 0.07710 -0.0168 0.0742 1.0000
16.500 1.2867 0.08872 0.08220 -0.0178 0.0734 1.0000
16.750 1.2713 0.09401 0.08775 -0.0192 0.0726 1.0000
17.000 1.2515 0.10003 0.09403 -0.0213 0.0722 1.0000
17.250 1.2210 0.10782 0.10214 -0.0246 0.0722 1.0000
17.500 1.1718 0.11917 0.11387 -0.0306 0.0733 1.0000
17.750 1.1064 0.13511 0.13016 -0.0401 0.0753 1.0000
18.000 1.0428 0.15377 0.14899 -0.0516 0.0773 1.0000
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Polar data table (+)
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