NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-212 (naca651212-il) Reynolds number: 100,000 Max Cl/Cd: 46.75 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651212-il-100000.txt Download as CSV file: xf-naca651212-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-212
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5648 0.09078 0.08598 -0.0434 1.0000 0.1444
-9.500 -0.5125 0.08985 0.08498 -0.0348 1.0000 0.1554
-9.250 -0.5602 0.08321 0.07848 -0.0434 1.0000 0.1584
-9.000 -0.5273 0.08160 0.07687 -0.0384 1.0000 0.1703
-8.750 -0.5692 0.07611 0.07149 -0.0431 1.0000 0.1721
-8.500 -0.5565 0.07337 0.06880 -0.0411 1.0000 0.1840
-8.250 -0.6001 0.06998 0.06544 -0.0410 1.0000 0.1867
-8.000 -0.6537 0.06880 0.06411 -0.0376 1.0000 0.1885
-6.250 -0.6694 0.03939 0.03224 -0.0196 1.0000 0.0913
-6.000 -0.6535 0.03617 0.02854 -0.0174 1.0000 0.0807
-5.750 -0.6361 0.03483 0.02631 -0.0147 1.0000 0.0738
-5.500 -0.6180 0.03191 0.02318 -0.0135 1.0000 0.0727
-5.250 -0.5994 0.03053 0.02146 -0.0122 1.0000 0.0735
-5.000 -0.5654 0.02810 0.01874 -0.0137 0.9964 0.0751
-4.750 -0.5294 0.02624 0.01674 -0.0153 0.9924 0.0760
-4.500 -0.4948 0.02477 0.01524 -0.0167 0.9878 0.0784
-4.250 -0.4572 0.02380 0.01421 -0.0188 0.9835 0.0841
-4.000 -0.4269 0.02273 0.01315 -0.0195 0.9779 0.0897
-3.750 -0.3938 0.02178 0.01231 -0.0210 0.9727 0.0980
-3.500 -0.3641 0.02099 0.01156 -0.0220 0.9674 0.1149
-3.250 -0.3385 0.01934 0.01055 -0.0227 0.9616 0.1967
-3.000 -0.3298 0.01840 0.01198 -0.0171 0.9562 0.7176
-2.750 -0.3164 0.01922 0.01278 -0.0125 0.9484 0.7615
-2.500 -0.2981 0.02045 0.01402 -0.0076 0.9429 0.8046
-2.250 -0.2947 0.02139 0.01498 -0.0002 0.9353 0.8426
-2.000 -0.2704 0.02280 0.01633 0.0053 0.9309 0.8824
-1.750 -0.2219 0.02323 0.01657 0.0019 0.9281 0.8973
-1.500 -0.1993 0.02316 0.01637 0.0021 0.9215 0.9063
-1.250 -0.1636 0.02316 0.01622 -0.0003 0.9164 0.9141
-1.000 -0.1149 0.02324 0.01616 -0.0050 0.9132 0.9194
-0.750 -0.0915 0.02324 0.01609 -0.0053 0.9066 0.9278
-0.500 -0.0496 0.02328 0.01603 -0.0089 0.9020 0.9335
-0.250 0.0047 0.02339 0.01606 -0.0147 0.8991 0.9376
0.000 0.0297 0.02346 0.01609 -0.0154 0.8927 0.9460
0.250 0.0803 0.02357 0.01616 -0.0208 0.8886 0.9501
0.500 0.1308 0.02365 0.01622 -0.0260 0.8853 0.9551
0.750 0.1792 0.02373 0.01630 -0.0309 0.8819 0.9598
1.000 0.2131 0.02390 0.01650 -0.0335 0.8751 0.9667
1.250 0.2601 0.02398 0.01662 -0.0381 0.8712 0.9721
1.500 0.3203 0.02394 0.01665 -0.0450 0.8687 0.9748
1.750 0.3473 0.02426 0.01703 -0.0465 0.8609 0.9837
2.000 0.4017 0.02423 0.01712 -0.0524 0.8568 0.9875
2.250 0.4573 0.02408 0.01709 -0.0582 0.8535 0.9912
2.500 0.4916 0.02434 0.01750 -0.0610 0.8446 0.9990
2.750 0.5336 0.02413 0.01742 -0.0638 0.8392 1.0000
3.000 0.5282 0.02467 0.01802 -0.0591 0.8273 1.0000
3.250 0.5346 0.02498 0.01840 -0.0561 0.8170 1.0000
3.500 0.5738 0.02455 0.01814 -0.0576 0.8094 1.0000
3.750 0.6521 0.02030 0.01407 -0.0589 0.7745 1.0000
4.000 0.6782 0.01778 0.01153 -0.0538 0.7372 1.0000
4.250 0.6935 0.01685 0.01067 -0.0499 0.7099 1.0000
4.500 0.7080 0.01594 0.00979 -0.0458 0.6750 1.0000
4.750 0.7116 0.01522 0.00897 -0.0397 0.6009 1.0000
5.000 0.6896 0.01610 0.00839 -0.0299 0.3340 1.0000
5.250 0.6650 0.01824 0.00929 -0.0220 0.1606 1.0000
5.500 0.6647 0.01978 0.01036 -0.0177 0.1163 1.0000
5.750 0.6756 0.02092 0.01139 -0.0153 0.0991 1.0000
6.000 0.6892 0.02216 0.01255 -0.0133 0.0896 1.0000
6.250 0.7089 0.02337 0.01372 -0.0120 0.0830 1.0000
6.500 0.7351 0.02513 0.01530 -0.0119 0.0774 1.0000
6.750 0.7631 0.02643 0.01669 -0.0118 0.0723 1.0000
7.000 0.7947 0.02822 0.01853 -0.0123 0.0694 1.0000
7.250 0.8276 0.03050 0.02085 -0.0130 0.0676 1.0000
7.500 0.8588 0.03334 0.02382 -0.0135 0.0665 1.0000
7.750 0.8833 0.03622 0.02699 -0.0131 0.0651 1.0000
8.000 0.9042 0.03857 0.02973 -0.0120 0.0646 1.0000
8.250 0.9267 0.04277 0.03419 -0.0116 0.0655 1.0000
8.500 0.9389 0.04438 0.03671 -0.0082 0.0701 1.0000
8.750 0.9513 0.04934 0.04212 -0.0064 0.0760 1.0000
11.000 0.7228 0.11241 0.10767 -0.0173 0.1713 1.0000
11.250 0.7366 0.11555 0.11084 -0.0165 0.1646 1.0000
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Polar data table (+)
Polar graphs
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