NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-410 (naca65410-il) Reynolds number: 50,000 Max Cl/Cd: 35.38 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65410-il-50000-n5.txt Download as CSV file: xf-naca65410-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-410
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4435 0.09016 0.08327 -0.0446 1.0000 0.0666
-8.250 -0.4730 0.08113 0.07444 -0.0498 1.0000 0.0572
-8.000 -0.4782 0.07773 0.07111 -0.0495 1.0000 0.0558
-7.750 -0.4865 0.07436 0.06776 -0.0492 1.0000 0.0545
-7.500 -0.4957 0.07095 0.06436 -0.0487 1.0000 0.0533
-7.250 -0.5043 0.06756 0.06092 -0.0479 1.0000 0.0520
-7.000 -0.5111 0.06407 0.05732 -0.0470 1.0000 0.0507
-6.750 -0.5156 0.06037 0.05341 -0.0461 1.0000 0.0493
-6.500 -0.5163 0.05652 0.04923 -0.0453 1.0000 0.0479
-6.250 -0.5118 0.05325 0.04567 -0.0443 1.0000 0.0479
-6.000 -0.5041 0.05054 0.04279 -0.0433 1.0000 0.0494
-5.750 -0.4940 0.04779 0.03976 -0.0425 1.0000 0.0510
-5.500 -0.4810 0.04487 0.03647 -0.0419 1.0000 0.0520
-5.250 -0.4651 0.04191 0.03302 -0.0413 1.0000 0.0520
-5.000 -0.4467 0.03915 0.02980 -0.0408 1.0000 0.0521
-4.750 -0.4246 0.03662 0.02679 -0.0406 0.9994 0.0526
-4.500 -0.3902 0.03427 0.02386 -0.0424 0.9947 0.0559
-4.250 -0.3558 0.03241 0.02135 -0.0437 0.9898 0.0589
-4.000 -0.3228 0.03029 0.01903 -0.0449 0.9858 0.0608
-3.750 -0.2920 0.02883 0.01738 -0.0454 0.9807 0.0633
-3.500 -0.2593 0.02782 0.01618 -0.0463 0.9763 0.0700
-3.250 -0.2306 0.02680 0.01502 -0.0463 0.9708 0.0751
-3.000 -0.1987 0.02591 0.01400 -0.0473 0.9659 0.0808
-2.750 -0.1695 0.02513 0.01305 -0.0481 0.9600 0.0908
-2.500 -0.1374 0.02431 0.01221 -0.0497 0.9546 0.1107
-2.250 -0.1034 0.02250 0.01123 -0.0525 0.9506 0.2390
-2.000 -0.1051 0.02138 0.01233 -0.0444 0.9432 0.7483
-1.750 -0.0959 0.02175 0.01276 -0.0377 0.9368 0.8487
-1.500 -0.0282 0.02207 0.01277 -0.0410 0.9385 0.9729
-1.250 0.0180 0.02205 0.01241 -0.0457 0.9336 0.9845
-1.000 0.0629 0.02205 0.01212 -0.0503 0.9285 0.9983
-0.750 0.0902 0.02210 0.01198 -0.0515 0.9218 1.0000
-0.500 0.1075 0.02216 0.01190 -0.0509 0.9127 1.0000
-0.250 0.1283 0.02227 0.01187 -0.0508 0.9051 1.0000
0.000 0.1530 0.02243 0.01188 -0.0513 0.8979 1.0000
0.250 0.1781 0.02263 0.01196 -0.0519 0.8910 1.0000
0.500 0.2048 0.02286 0.01210 -0.0526 0.8843 1.0000
0.750 0.2360 0.02312 0.01226 -0.0541 0.8788 1.0000
1.000 0.2595 0.02343 0.01251 -0.0542 0.8712 1.0000
1.250 0.2950 0.02369 0.01273 -0.0563 0.8667 1.0000
1.500 0.3154 0.02409 0.01310 -0.0559 0.8583 1.0000
1.750 0.3496 0.02438 0.01341 -0.0576 0.8533 1.0000
2.000 0.3718 0.02482 0.01386 -0.0574 0.8454 1.0000
2.250 0.4042 0.02515 0.01423 -0.0588 0.8398 1.0000
2.500 0.4282 0.02561 0.01474 -0.0589 0.8322 1.0000
2.750 0.4592 0.02597 0.01521 -0.0600 0.8259 1.0000
3.000 0.4842 0.02643 0.01577 -0.0601 0.8182 1.0000
3.250 0.5153 0.02679 0.01626 -0.0611 0.8114 1.0000
3.500 0.5393 0.02727 0.01691 -0.0609 0.8026 1.0000
3.750 0.5743 0.02750 0.01734 -0.0623 0.7959 1.0000
4.000 0.5969 0.02797 0.01799 -0.0618 0.7853 1.0000
4.250 0.6269 0.02825 0.01850 -0.0622 0.7762 1.0000
4.500 0.6603 0.02836 0.01894 -0.0628 0.7671 1.0000
4.750 0.6864 0.02859 0.01945 -0.0624 0.7545 1.0000
5.000 0.7336 0.02621 0.01745 -0.0608 0.7193 1.0000
5.250 0.7621 0.02247 0.01367 -0.0534 0.6060 1.0000
5.500 0.7811 0.02208 0.01241 -0.0486 0.3928 1.0000
5.750 0.7716 0.02510 0.01371 -0.0437 0.1720 1.0000
6.000 0.7754 0.02745 0.01540 -0.0411 0.1104 1.0000
6.250 0.7869 0.02912 0.01698 -0.0392 0.0917 1.0000
6.500 0.7996 0.03069 0.01856 -0.0373 0.0827 1.0000
6.750 0.8155 0.03211 0.02007 -0.0358 0.0741 1.0000
7.000 0.8359 0.03359 0.02170 -0.0348 0.0668 1.0000
7.250 0.8678 0.03520 0.02347 -0.0349 0.0618 1.0000
7.500 0.9099 0.03735 0.02566 -0.0363 0.0573 1.0000
7.750 0.9439 0.03935 0.02800 -0.0368 0.0524 1.0000
8.000 0.9760 0.04186 0.03082 -0.0373 0.0498 1.0000
8.250 1.0041 0.04477 0.03400 -0.0374 0.0482 1.0000
8.500 1.0277 0.04811 0.03764 -0.0371 0.0472 1.0000
8.750 1.0455 0.05185 0.04171 -0.0363 0.0462 1.0000
9.000 1.0544 0.05486 0.04533 -0.0342 0.0451 1.0000
9.250 1.0591 0.05813 0.04915 -0.0320 0.0438 1.0000
9.500 1.0600 0.06165 0.05313 -0.0298 0.0429 1.0000
9.750 1.0573 0.06537 0.05725 -0.0276 0.0426 1.0000
10.000 1.0503 0.06915 0.06138 -0.0254 0.0426 1.0000
10.250 1.0382 0.07276 0.06527 -0.0230 0.0427 1.0000
10.500 1.0231 0.07654 0.06929 -0.0211 0.0428 1.0000
10.750 1.0057 0.08066 0.07362 -0.0201 0.0430 1.0000
11.000 0.9865 0.08526 0.07841 -0.0201 0.0432 1.0000
11.250 0.9664 0.09042 0.08374 -0.0213 0.0435 1.0000
11.500 0.9463 0.09626 0.08970 -0.0236 0.0438 1.0000
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Polar data table (+)
Polar graphs
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