NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-210 (naca64210-il) Reynolds number: 500,000 Max Cl/Cd: 76.28 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64210-il-500000.txt Download as CSV file: xf-naca64210-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5584 0.08391 0.08163 -0.0289 1.0000 0.0222
-9.750 -0.5710 0.07522 0.07290 -0.0366 1.0000 0.0222
-9.500 -0.5877 0.06939 0.06699 -0.0412 1.0000 0.0222
-9.250 -0.6052 0.06521 0.06273 -0.0433 1.0000 0.0222
-9.000 -0.6203 0.06183 0.05926 -0.0431 1.0000 0.0222
-8.750 -0.6297 0.05793 0.05519 -0.0431 1.0000 0.0222
-8.500 -0.6354 0.05395 0.05099 -0.0427 1.0000 0.0223
-8.250 -0.6575 0.04491 0.04165 -0.0423 1.0000 0.0229
-8.000 -0.6510 0.04149 0.03815 -0.0417 1.0000 0.0235
-7.750 -0.6402 0.03915 0.03571 -0.0408 1.0000 0.0240
-7.500 -0.6295 0.03704 0.03349 -0.0395 1.0000 0.0246
-7.250 -0.6204 0.03477 0.03105 -0.0377 1.0000 0.0253
-7.000 -0.6218 0.02619 0.02162 -0.0336 0.9989 0.0192
-6.750 -0.5892 0.02315 0.01817 -0.0355 0.9950 0.0200
-6.500 -0.5574 0.02018 0.01481 -0.0368 0.9907 0.0202
-6.250 -0.5233 0.01823 0.01259 -0.0384 0.9867 0.0208
-6.000 -0.4875 0.01686 0.01102 -0.0403 0.9837 0.0216
-5.750 -0.4544 0.01552 0.00951 -0.0416 0.9784 0.0227
-5.500 -0.4223 0.01387 0.00781 -0.0430 0.9729 0.0243
-5.250 -0.3890 0.01306 0.00696 -0.0444 0.9667 0.0256
-5.000 -0.3576 0.01236 0.00621 -0.0453 0.9584 0.0272
-4.750 -0.3286 0.01182 0.00561 -0.0456 0.9486 0.0290
-4.500 -0.3008 0.01138 0.00510 -0.0456 0.9385 0.0308
-4.250 -0.2768 0.01052 0.00417 -0.0451 0.9273 0.0344
-4.000 -0.2515 0.01016 0.00375 -0.0445 0.9159 0.0379
-3.750 -0.2258 0.00980 0.00331 -0.0441 0.9053 0.0425
-3.500 -0.2001 0.00945 0.00294 -0.0437 0.8954 0.0518
-3.250 -0.1747 0.00892 0.00254 -0.0433 0.8851 0.0921
-3.000 -0.1533 0.00728 0.00202 -0.0433 0.8743 0.3822
-2.750 -0.1286 0.00671 0.00193 -0.0430 0.8649 0.5336
-2.500 -0.1020 0.00658 0.00187 -0.0427 0.8557 0.5813
-2.250 -0.0748 0.00650 0.00182 -0.0425 0.8459 0.6115
-2.000 -0.0475 0.00646 0.00177 -0.0422 0.8368 0.6317
-1.750 -0.0204 0.00643 0.00175 -0.0420 0.8273 0.6574
-1.500 0.0063 0.00641 0.00180 -0.0416 0.8180 0.6920
-1.250 0.0334 0.00644 0.00182 -0.0412 0.8095 0.7145
-1.000 0.0611 0.00644 0.00180 -0.0411 0.8000 0.7268
-0.750 0.0887 0.00643 0.00179 -0.0410 0.7911 0.7364
-0.500 0.1165 0.00644 0.00176 -0.0409 0.7824 0.7454
-0.250 0.1445 0.00644 0.00175 -0.0409 0.7729 0.7550
0.000 0.1722 0.00645 0.00176 -0.0408 0.7647 0.7639
0.250 0.2001 0.00646 0.00177 -0.0408 0.7558 0.7734
0.500 0.2279 0.00648 0.00179 -0.0407 0.7472 0.7830
0.750 0.2555 0.00650 0.00182 -0.0406 0.7389 0.7923
1.000 0.2834 0.00652 0.00186 -0.0405 0.7300 0.8025
1.250 0.3108 0.00656 0.00191 -0.0404 0.7214 0.8126
1.500 0.3380 0.00658 0.00196 -0.0402 0.7112 0.8221
1.750 0.3655 0.00661 0.00202 -0.0400 0.7011 0.8322
2.000 0.3922 0.00664 0.00205 -0.0396 0.6851 0.8429
2.250 0.4176 0.00667 0.00205 -0.0389 0.6591 0.8532
2.500 0.4432 0.00673 0.00208 -0.0383 0.6361 0.8639
2.750 0.4693 0.00679 0.00214 -0.0379 0.6154 0.8750
3.000 0.4949 0.00688 0.00223 -0.0373 0.5943 0.8865
3.250 0.5197 0.00696 0.00233 -0.0365 0.5707 0.8981
3.500 0.5431 0.00712 0.00242 -0.0355 0.5340 0.9107
3.750 0.5642 0.00746 0.00253 -0.0341 0.4634 0.9248
4.000 0.5772 0.00872 0.00297 -0.0318 0.2657 0.9430
4.250 0.5939 0.01008 0.00356 -0.0304 0.0954 0.9648
4.500 0.6260 0.01084 0.00407 -0.0318 0.0482 0.9900
4.750 0.6539 0.01130 0.00453 -0.0322 0.0393 1.0000
5.000 0.6788 0.01200 0.00526 -0.0320 0.0331 1.0000
5.250 0.7049 0.01247 0.00576 -0.0319 0.0302 1.0000
5.500 0.7299 0.01305 0.00636 -0.0317 0.0277 1.0000
5.750 0.7507 0.01422 0.00757 -0.0308 0.0252 1.0000
6.000 0.7750 0.01489 0.00830 -0.0304 0.0239 1.0000
6.250 0.7992 0.01558 0.00904 -0.0299 0.0228 1.0000
6.500 0.8228 0.01640 0.00992 -0.0294 0.0218 1.0000
6.750 0.8464 0.01729 0.01086 -0.0288 0.0210 1.0000
7.000 0.8701 0.01822 0.01185 -0.0283 0.0202 1.0000
7.250 0.8935 0.01931 0.01300 -0.0278 0.0195 1.0000
7.500 0.9161 0.02099 0.01474 -0.0273 0.0187 1.0000
7.750 0.9378 0.02366 0.01763 -0.0266 0.0178 1.0000
8.000 0.9606 0.02499 0.01915 -0.0260 0.0175 1.0000
8.250 0.9817 0.02691 0.02132 -0.0251 0.0172 1.0000
8.500 1.0006 0.02930 0.02400 -0.0240 0.0169 1.0000
8.750 1.0154 0.03257 0.02764 -0.0225 0.0168 1.0000
9.000 1.0252 0.03635 0.03183 -0.0206 0.0169 1.0000
9.250 1.0318 0.04010 0.03596 -0.0185 0.0166 1.0000
9.500 1.0305 0.04469 0.04092 -0.0161 0.0169 1.0000
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Polar data table (+)
Polar graphs
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