NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-210 (naca64210-il) Reynolds number: 100,000 Max Cl/Cd: 44.59 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64210-il-100000-n5.txt Download as CSV file: xf-naca64210-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5647 0.09085 0.08579 -0.0230 1.0000 0.0284
-9.750 -0.5706 0.08447 0.07945 -0.0273 1.0000 0.0284
-9.500 -0.5803 0.07716 0.07218 -0.0331 1.0000 0.0279
-9.250 -0.5951 0.07077 0.06577 -0.0380 1.0000 0.0275
-9.000 -0.6126 0.06581 0.06076 -0.0406 1.0000 0.0272
-8.750 -0.6262 0.06142 0.05624 -0.0415 1.0000 0.0270
-8.500 -0.6339 0.05710 0.05172 -0.0420 1.0000 0.0273
-8.250 -0.6366 0.05299 0.04736 -0.0419 1.0000 0.0278
-8.000 -0.6353 0.04906 0.04311 -0.0414 1.0000 0.0286
-7.750 -0.6306 0.04524 0.03891 -0.0405 1.0000 0.0290
-7.500 -0.6229 0.04158 0.03485 -0.0394 1.0000 0.0292
-7.250 -0.6123 0.03829 0.03114 -0.0381 1.0000 0.0295
-7.000 -0.5994 0.03535 0.02776 -0.0367 1.0000 0.0299
-6.750 -0.5844 0.03287 0.02484 -0.0352 1.0000 0.0304
-6.500 -0.5689 0.03059 0.02219 -0.0338 1.0000 0.0319
-6.250 -0.5528 0.02867 0.02012 -0.0326 1.0000 0.0337
-6.000 -0.5351 0.02701 0.01825 -0.0312 1.0000 0.0347
-5.750 -0.5170 0.02545 0.01649 -0.0297 1.0000 0.0358
-5.500 -0.4988 0.02407 0.01495 -0.0282 1.0000 0.0369
-5.250 -0.4806 0.02285 0.01359 -0.0266 1.0000 0.0383
-5.000 -0.4509 0.02178 0.01233 -0.0273 0.9956 0.0416
-4.750 -0.4177 0.02037 0.01087 -0.0288 0.9888 0.0449
-4.500 -0.3842 0.01927 0.00977 -0.0305 0.9818 0.0484
-4.250 -0.3489 0.01843 0.00881 -0.0324 0.9752 0.0540
-4.000 -0.3160 0.01757 0.00792 -0.0340 0.9672 0.0625
-3.750 -0.2810 0.01678 0.00709 -0.0358 0.9605 0.0751
-3.500 -0.2480 0.01582 0.00635 -0.0375 0.9527 0.1167
-3.250 -0.2232 0.01370 0.00577 -0.0386 0.9441 0.4272
-3.000 -0.1935 0.01332 0.00586 -0.0387 0.9365 0.5844
-2.750 -0.1675 0.01335 0.00610 -0.0375 0.9268 0.6642
-2.500 -0.1433 0.01365 0.00656 -0.0353 0.9184 0.7316
-2.250 -0.1160 0.01373 0.00658 -0.0344 0.9093 0.7540
-2.000 -0.0868 0.01368 0.00640 -0.0346 0.9001 0.7658
-1.750 -0.0555 0.01362 0.00621 -0.0351 0.8924 0.7765
-1.500 -0.0282 0.01358 0.00610 -0.0348 0.8824 0.7852
-1.250 0.0008 0.01353 0.00594 -0.0349 0.8738 0.7950
-1.000 0.0291 0.01348 0.00583 -0.0349 0.8651 0.8048
-0.750 0.0561 0.01346 0.00576 -0.0345 0.8557 0.8139
-0.500 0.0846 0.01341 0.00566 -0.0345 0.8481 0.8241
-0.250 0.1105 0.01341 0.00563 -0.0340 0.8382 0.8348
0.000 0.1373 0.01339 0.00560 -0.0336 0.8298 0.8446
0.250 0.1640 0.01338 0.00557 -0.0332 0.8214 0.8553
0.500 0.1901 0.01339 0.00559 -0.0327 0.8125 0.8669
0.750 0.2173 0.01337 0.00557 -0.0323 0.8052 0.8786
1.000 0.2434 0.01339 0.00563 -0.0319 0.7958 0.8905
1.250 0.2715 0.01338 0.00566 -0.0317 0.7887 0.9026
1.500 0.2995 0.01341 0.00574 -0.0317 0.7798 0.9158
1.750 0.3299 0.01342 0.00580 -0.0322 0.7721 0.9290
2.000 0.3621 0.01345 0.00592 -0.0331 0.7640 0.9423
2.250 0.3968 0.01349 0.00604 -0.0346 0.7561 0.9555
2.500 0.4337 0.01350 0.00615 -0.0364 0.7477 0.9684
2.750 0.4710 0.01354 0.00633 -0.0385 0.7370 0.9830
3.000 0.5060 0.01359 0.00649 -0.0402 0.7266 1.0000
3.250 0.5274 0.01365 0.00660 -0.0389 0.7127 1.0000
3.500 0.5481 0.01352 0.00644 -0.0370 0.6835 1.0000
3.750 0.5673 0.01333 0.00608 -0.0344 0.6288 1.0000
4.000 0.5876 0.01341 0.00598 -0.0325 0.5661 1.0000
4.250 0.6096 0.01367 0.00610 -0.0312 0.5036 1.0000
4.500 0.6227 0.01480 0.00627 -0.0287 0.3163 1.0000
4.750 0.6328 0.01691 0.00725 -0.0270 0.1287 1.0000
5.000 0.6516 0.01814 0.00820 -0.0259 0.0816 1.0000
5.250 0.6723 0.01910 0.00910 -0.0251 0.0645 1.0000
5.500 0.6930 0.02006 0.01008 -0.0242 0.0564 1.0000
5.750 0.7138 0.02100 0.01105 -0.0233 0.0498 1.0000
6.000 0.7340 0.02206 0.01217 -0.0224 0.0451 1.0000
6.250 0.7549 0.02319 0.01341 -0.0214 0.0421 1.0000
6.500 0.7763 0.02444 0.01470 -0.0206 0.0397 1.0000
6.750 0.7982 0.02592 0.01616 -0.0200 0.0373 1.0000
7.000 0.8217 0.02754 0.01788 -0.0195 0.0350 1.0000
7.250 0.8463 0.02906 0.01961 -0.0190 0.0331 1.0000
7.500 0.8707 0.03099 0.02179 -0.0185 0.0318 1.0000
7.750 0.8941 0.03312 0.02418 -0.0180 0.0309 1.0000
8.000 0.9155 0.03547 0.02686 -0.0172 0.0301 1.0000
8.250 0.9345 0.03803 0.02976 -0.0163 0.0294 1.0000
8.500 0.9511 0.04038 0.03240 -0.0154 0.0284 1.0000
8.750 0.9655 0.04269 0.03490 -0.0146 0.0271 1.0000
9.000 0.9737 0.04666 0.03911 -0.0135 0.0260 1.0000
9.250 0.9798 0.04969 0.04265 -0.0118 0.0257 1.0000
9.500 0.9815 0.05320 0.04658 -0.0100 0.0255 1.0000
9.750 0.9785 0.05689 0.05065 -0.0082 0.0254 1.0000
10.000 0.9705 0.06061 0.05469 -0.0064 0.0253 1.0000
10.250 0.9566 0.06412 0.05845 -0.0043 0.0253 1.0000
10.500 0.9405 0.06789 0.06242 -0.0032 0.0253 1.0000
10.750 0.9227 0.07215 0.06687 -0.0034 0.0254 1.0000
11.000 0.9040 0.07706 0.07194 -0.0048 0.0255 1.0000
11.250 0.8852 0.08269 0.07770 -0.0075 0.0256 1.0000
11.500 0.8665 0.08919 0.08431 -0.0114 0.0257 1.0000
11.750 0.8498 0.09635 0.09154 -0.0159 0.0259 1.0000
12.000 0.8343 0.10449 0.09976 -0.0216 0.0262 1.0000
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Polar data table (+)
Polar graphs
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