NACA 64-108 AIRFOIL (n64108-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-108 AIRFOIL (n64108-il) Reynolds number: 50,000 Max Cl/Cd: 27.61 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64108-il-50000-n5.txt Download as CSV file: xf-n64108-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-108 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6347 0.08907 0.08224 -0.0186 1.0000 0.0490
-8.750 -0.6349 0.08456 0.07776 -0.0197 1.0000 0.0486
-8.500 -0.6345 0.08021 0.07342 -0.0207 1.0000 0.0480
-8.250 -0.6359 0.07577 0.06893 -0.0223 1.0000 0.0474
-8.000 -0.6368 0.07126 0.06434 -0.0237 1.0000 0.0467
-7.750 -0.6364 0.06671 0.05966 -0.0249 1.0000 0.0459
-7.500 -0.6336 0.06228 0.05504 -0.0258 1.0000 0.0451
-7.250 -0.6282 0.05789 0.05038 -0.0265 1.0000 0.0445
-7.000 -0.6200 0.05356 0.04571 -0.0267 1.0000 0.0440
-6.750 -0.6088 0.04943 0.04117 -0.0267 1.0000 0.0437
-6.500 -0.5946 0.04556 0.03684 -0.0264 1.0000 0.0436
-6.250 -0.5778 0.04208 0.03287 -0.0259 1.0000 0.0446
-6.000 -0.5586 0.03911 0.02926 -0.0252 1.0000 0.0476
-5.750 -0.5371 0.03645 0.02598 -0.0243 1.0000 0.0493
-5.500 -0.5150 0.03333 0.02256 -0.0237 1.0000 0.0503
-5.250 -0.4914 0.03086 0.01983 -0.0230 1.0000 0.0518
-5.000 -0.4668 0.02878 0.01745 -0.0221 1.0000 0.0539
-4.750 -0.4421 0.02707 0.01553 -0.0210 1.0000 0.0578
-4.500 -0.4183 0.02561 0.01391 -0.0199 1.0000 0.0646
-4.250 -0.3958 0.02426 0.01248 -0.0187 1.0000 0.0704
-4.000 -0.3738 0.02306 0.01108 -0.0172 1.0000 0.0761
-3.750 -0.3534 0.02188 0.00986 -0.0161 1.0000 0.0882
-3.500 -0.3331 0.02062 0.00864 -0.0153 1.0000 0.1101
-3.250 -0.3149 0.01889 0.00737 -0.0143 1.0000 0.1728
-3.000 -0.3129 0.01654 0.00739 -0.0092 1.0000 0.6149
-2.750 -0.3076 0.01658 0.00784 -0.0021 1.0000 0.7575
-2.500 -0.2982 0.01718 0.00863 0.0070 1.0000 0.8781
-2.250 -0.2527 0.01724 0.00828 0.0052 1.0000 0.9194
-2.000 -0.2151 0.01698 0.00766 0.0028 1.0000 0.9364
-1.750 -0.1749 0.01675 0.00715 -0.0003 1.0000 0.9519
-1.500 -0.1303 0.01652 0.00668 -0.0044 1.0000 0.9658
-1.250 -0.0856 0.01629 0.00623 -0.0087 1.0000 0.9800
-1.000 -0.0436 0.01607 0.00587 -0.0127 1.0000 0.9970
-0.750 -0.0418 0.01596 0.00572 -0.0097 1.0000 1.0000
-0.500 -0.0461 0.01589 0.00561 -0.0056 1.0000 1.0000
-0.250 -0.0432 0.01591 0.00554 -0.0026 1.0000 1.0000
0.000 -0.0192 0.01606 0.00558 -0.0033 0.9942 1.0000
0.250 0.0204 0.01629 0.00574 -0.0068 0.9821 1.0000
0.500 0.0595 0.01653 0.00594 -0.0100 0.9706 1.0000
0.750 0.0983 0.01678 0.00620 -0.0130 0.9593 1.0000
1.000 0.1375 0.01703 0.00648 -0.0160 0.9485 1.0000
1.250 0.1779 0.01729 0.00680 -0.0192 0.9384 1.0000
1.500 0.2144 0.01755 0.00716 -0.0215 0.9270 1.0000
1.750 0.2497 0.01782 0.00758 -0.0235 0.9154 1.0000
2.000 0.2840 0.01810 0.00800 -0.0253 0.9039 1.0000
2.250 0.3180 0.01839 0.00847 -0.0268 0.8923 1.0000
2.500 0.3515 0.01867 0.00902 -0.0282 0.8805 1.0000
2.750 0.3836 0.01894 0.00954 -0.0290 0.8669 1.0000
3.000 0.4138 0.01919 0.01007 -0.0294 0.8512 1.0000
3.250 0.4471 0.01914 0.01035 -0.0291 0.8282 1.0000
3.500 0.4671 0.01764 0.00881 -0.0210 0.7200 1.0000
3.750 0.4802 0.01739 0.00811 -0.0149 0.5690 1.0000
4.000 0.4844 0.01955 0.00827 -0.0102 0.2038 1.0000
4.250 0.5008 0.02190 0.00984 -0.0093 0.1105 1.0000
4.500 0.5212 0.02335 0.01121 -0.0084 0.0871 1.0000
4.750 0.5420 0.02482 0.01270 -0.0074 0.0777 1.0000
5.000 0.5653 0.02611 0.01418 -0.0064 0.0684 1.0000
5.250 0.5898 0.02759 0.01584 -0.0056 0.0604 1.0000
5.500 0.6169 0.02932 0.01775 -0.0048 0.0565 1.0000
5.750 0.6441 0.03142 0.01998 -0.0042 0.0537 1.0000
6.000 0.6705 0.03426 0.02294 -0.0038 0.0518 1.0000
6.250 0.6952 0.03660 0.02589 -0.0029 0.0493 1.0000
6.500 0.7172 0.03915 0.02898 -0.0021 0.0454 1.0000
6.750 0.7371 0.04227 0.03258 -0.0012 0.0439 1.0000
7.000 0.7544 0.04579 0.03669 -0.0003 0.0434 1.0000
7.250 0.7685 0.04960 0.04100 0.0005 0.0432 1.0000
7.500 0.7792 0.05373 0.04560 0.0013 0.0433 1.0000
7.750 0.7863 0.05806 0.05036 0.0019 0.0437 1.0000
8.000 0.7893 0.06255 0.05522 0.0022 0.0440 1.0000
8.250 0.7887 0.06702 0.05999 0.0021 0.0441 1.0000
8.500 0.7843 0.07151 0.06471 0.0017 0.0440 1.0000
8.750 0.7756 0.07620 0.06957 0.0008 0.0443 1.0000
9.000 0.7627 0.08083 0.07428 -0.0006 0.0451 1.0000
9.250 0.7495 0.08604 0.07952 -0.0034 0.0458 1.0000
9.500 0.7392 0.09194 0.08541 -0.0075 0.0470 1.0000
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Polar data table (+)
Polar graphs
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