NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-212 (naca651212-il) Reynolds number: 200,000 Max Cl/Cd: 55.93 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651212-il-200000.txt Download as CSV file: xf-naca651212-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5424 0.08422 0.08068 -0.0459 1.0000 0.0588
-10.000 -0.5642 0.07758 0.07402 -0.0514 1.0000 0.0590
-9.750 -0.5884 0.07283 0.06920 -0.0540 1.0000 0.0592
-9.500 -0.6150 0.06975 0.06604 -0.0535 1.0000 0.0595
-9.250 -0.6465 0.06822 0.06428 -0.0508 1.0000 0.0602
-9.000 -0.6632 0.06705 0.06287 -0.0477 1.0000 0.0606
-8.750 -0.6772 0.06552 0.06117 -0.0438 1.0000 0.0607
-8.500 -0.6766 0.05684 0.05277 -0.0437 1.0000 0.0628
-8.250 -0.6814 0.05507 0.05106 -0.0400 1.0000 0.0639
-8.000 -0.6901 0.05364 0.04962 -0.0359 1.0000 0.0651
-7.750 -0.6835 0.05141 0.04726 -0.0351 0.9976 0.0690
-7.500 -0.6654 0.04691 0.04229 -0.0382 0.9905 0.0769
-7.250 -0.6366 0.04398 0.03926 -0.0407 0.9858 0.0823
-7.000 -0.6136 0.04049 0.03543 -0.0429 0.9797 0.0918
-6.750 -0.5792 0.03199 0.02536 -0.0410 0.9740 0.0477
-6.500 -0.5450 0.02848 0.02148 -0.0430 0.9711 0.0470
-6.250 -0.5148 0.02584 0.01854 -0.0438 0.9654 0.0464
-6.000 -0.4793 0.02354 0.01595 -0.0454 0.9615 0.0459
-5.750 -0.4405 0.02174 0.01393 -0.0475 0.9590 0.0463
-5.500 -0.4001 0.02066 0.01267 -0.0500 0.9567 0.0482
-5.250 -0.3721 0.01891 0.01092 -0.0502 0.9501 0.0504
-5.000 -0.3385 0.01769 0.00973 -0.0516 0.9456 0.0529
-4.750 -0.3036 0.01675 0.00878 -0.0533 0.9420 0.0563
-4.500 -0.2795 0.01626 0.00823 -0.0528 0.9333 0.0605
-4.250 -0.2515 0.01525 0.00726 -0.0533 0.9282 0.0682
-4.000 -0.2297 0.01467 0.00664 -0.0524 0.9194 0.0783
-3.750 -0.2112 0.01290 0.00573 -0.0517 0.9131 0.2445
-3.500 -0.2063 0.01144 0.00585 -0.0479 0.9032 0.6196
-3.250 -0.1795 0.01158 0.00603 -0.0469 0.8985 0.6712
-3.000 -0.1566 0.01181 0.00624 -0.0455 0.8908 0.6996
-2.750 -0.1318 0.01212 0.00658 -0.0438 0.8854 0.7288
-2.500 -0.1109 0.01270 0.00722 -0.0410 0.8793 0.7585
-2.250 -0.0890 0.01312 0.00765 -0.0386 0.8730 0.7783
-2.000 -0.0633 0.01326 0.00774 -0.0375 0.8687 0.7891
-1.750 -0.0384 0.01325 0.00764 -0.0372 0.8615 0.7975
-1.500 -0.0118 0.01322 0.00757 -0.0367 0.8563 0.8018
-1.250 0.0156 0.01318 0.00746 -0.0365 0.8522 0.8074
-1.000 0.0409 0.01316 0.00740 -0.0364 0.8451 0.8139
-0.750 0.0676 0.01313 0.00734 -0.0360 0.8404 0.8183
-0.500 0.0943 0.01312 0.00729 -0.0359 0.8356 0.8245
-0.250 0.1199 0.01313 0.00728 -0.0357 0.8293 0.8301
0.000 0.1468 0.01310 0.00724 -0.0353 0.8250 0.8351
0.250 0.1735 0.01312 0.00724 -0.0355 0.8199 0.8422
0.500 0.1981 0.01316 0.00731 -0.0348 0.8140 0.8470
0.750 0.2253 0.01314 0.00729 -0.0346 0.8099 0.8530
1.000 0.2511 0.01319 0.00736 -0.0344 0.8048 0.8594
1.250 0.2755 0.01326 0.00748 -0.0338 0.7990 0.8652
1.500 0.3032 0.01325 0.00746 -0.0338 0.7949 0.8726
1.750 0.3273 0.01332 0.00760 -0.0331 0.7897 0.8780
2.000 0.3521 0.01340 0.00774 -0.0327 0.7839 0.8859
2.250 0.3783 0.01337 0.00775 -0.0321 0.7797 0.8919
2.500 0.4021 0.01345 0.00791 -0.0315 0.7733 0.9000
2.750 0.4272 0.01340 0.00791 -0.0307 0.7669 0.9068
3.000 0.4529 0.01334 0.00792 -0.0300 0.7608 0.9155
3.250 0.4786 0.01307 0.00770 -0.0290 0.7505 0.9226
3.500 0.5049 0.01250 0.00709 -0.0275 0.7337 0.9311
3.750 0.5300 0.01185 0.00643 -0.0257 0.7066 0.9387
4.000 0.5559 0.01145 0.00604 -0.0247 0.6810 0.9477
4.250 0.5852 0.01123 0.00583 -0.0245 0.6578 0.9566
4.500 0.6175 0.01104 0.00563 -0.0251 0.6152 0.9638
4.750 0.6397 0.01150 0.00541 -0.0239 0.4400 0.9740
5.000 0.6441 0.01526 0.00705 -0.0227 0.0812 0.9882
5.250 0.6780 0.01641 0.00817 -0.0249 0.0630 0.9977
5.500 0.6847 0.01686 0.00864 -0.0218 0.0582 1.0000
5.750 0.6881 0.01773 0.00946 -0.0183 0.0536 1.0000
6.000 0.7063 0.01846 0.01024 -0.0171 0.0507 1.0000
6.250 0.7261 0.01938 0.01117 -0.0161 0.0480 1.0000
6.500 0.7476 0.02043 0.01221 -0.0154 0.0459 1.0000
6.750 0.7716 0.02177 0.01350 -0.0152 0.0439 1.0000
7.000 0.8002 0.02375 0.01551 -0.0156 0.0417 1.0000
7.250 0.8277 0.02504 0.01693 -0.0156 0.0406 1.0000
7.500 0.8563 0.02679 0.01884 -0.0157 0.0400 1.0000
7.750 0.8841 0.02894 0.02121 -0.0157 0.0399 1.0000
8.000 0.9097 0.03157 0.02412 -0.0154 0.0403 1.0000
8.250 0.9316 0.03413 0.02698 -0.0146 0.0403 1.0000
8.500 0.9503 0.03680 0.02997 -0.0135 0.0401 1.0000
8.750 0.9737 0.04149 0.03479 -0.0134 0.0429 1.0000
11.000 0.7424 0.07904 0.07589 0.0082 0.0743 1.0000
11.250 0.7070 0.08775 0.08467 0.0039 0.0753 1.0000
11.500 0.6706 0.09873 0.09569 -0.0031 0.0757 1.0000
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Polar data table (+)
Polar graphs
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