NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 50,000 Max Cl/Cd: 29.32 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca641112-il-50000-n5.txt Download as CSV file: xf-naca641112-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-112
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6383 0.10078 0.09348 -0.0219 1.0000 0.0542
-11.250 -0.6502 0.09394 0.08665 -0.0263 1.0000 0.0539
-11.000 -0.6647 0.08749 0.08018 -0.0304 1.0000 0.0536
-10.750 -0.6810 0.08160 0.07425 -0.0339 1.0000 0.0532
-10.500 -0.6991 0.07635 0.06893 -0.0366 1.0000 0.0528
-10.250 -0.7182 0.07181 0.06427 -0.0380 1.0000 0.0526
-10.000 -0.7361 0.06797 0.06030 -0.0379 1.0000 0.0526
-9.750 -0.7492 0.06432 0.05644 -0.0373 1.0000 0.0526
-9.500 -0.7576 0.06064 0.05249 -0.0364 1.0000 0.0528
-9.250 -0.7611 0.05705 0.04858 -0.0354 1.0000 0.0529
-9.000 -0.7598 0.05358 0.04475 -0.0342 1.0000 0.0531
-8.750 -0.7547 0.05026 0.04102 -0.0330 1.0000 0.0534
-8.500 -0.7459 0.04713 0.03746 -0.0318 1.0000 0.0539
-8.250 -0.7338 0.04433 0.03418 -0.0305 1.0000 0.0547
-8.000 -0.7170 0.04175 0.03156 -0.0299 1.0000 0.0567
-7.750 -0.6992 0.03975 0.02939 -0.0291 1.0000 0.0594
-7.500 -0.6799 0.03769 0.02707 -0.0282 1.0000 0.0619
-7.250 -0.6578 0.03564 0.02472 -0.0273 1.0000 0.0640
-7.000 -0.6340 0.03390 0.02265 -0.0263 1.0000 0.0666
-6.750 -0.6117 0.03229 0.02118 -0.0255 1.0000 0.0711
-6.500 -0.5894 0.03104 0.01980 -0.0244 1.0000 0.0762
-6.250 -0.5673 0.02985 0.01847 -0.0230 1.0000 0.0805
-6.000 -0.5524 0.02874 0.01745 -0.0211 1.0000 0.0867
-5.750 -0.5391 0.02780 0.01643 -0.0189 1.0000 0.0945
-5.500 -0.5298 0.02678 0.01547 -0.0164 1.0000 0.1021
-5.250 -0.5218 0.02579 0.01449 -0.0137 1.0000 0.1125
-5.000 -0.5148 0.02474 0.01356 -0.0110 1.0000 0.1299
-4.750 -0.5087 0.02345 0.01254 -0.0085 1.0000 0.1621
-4.500 -0.5058 0.02147 0.01144 -0.0061 1.0000 0.2710
-4.250 -0.5041 0.02053 0.01178 -0.0016 1.0000 0.4948
-4.000 -0.4773 0.02092 0.01228 -0.0006 0.9901 0.5980
-3.750 -0.4505 0.02197 0.01337 0.0018 0.9794 0.6680
-3.500 -0.4250 0.02327 0.01464 0.0053 0.9696 0.7210
-3.250 -0.3907 0.02400 0.01521 0.0060 0.9619 0.7480
-3.000 -0.3571 0.02403 0.01497 0.0050 0.9524 0.7611
-2.750 -0.3221 0.02393 0.01464 0.0032 0.9436 0.7722
-2.500 -0.2852 0.02382 0.01432 0.0010 0.9355 0.7832
-2.250 -0.2503 0.02378 0.01410 -0.0004 0.9267 0.7916
-2.000 -0.2128 0.02364 0.01378 -0.0028 0.9193 0.8011
-1.750 -0.1817 0.02356 0.01358 -0.0038 0.9097 0.8091
-1.500 -0.1465 0.02344 0.01332 -0.0056 0.9021 0.8176
-1.250 -0.1170 0.02337 0.01315 -0.0063 0.8926 0.8260
-1.000 -0.0856 0.02330 0.01300 -0.0074 0.8844 0.8343
-0.750 -0.0554 0.02323 0.01285 -0.0083 0.8760 0.8436
-0.500 -0.0253 0.02322 0.01280 -0.0090 0.8674 0.8516
-0.250 0.0053 0.02316 0.01270 -0.0099 0.8599 0.8613
0.000 0.0343 0.02319 0.01271 -0.0105 0.8511 0.8700
0.250 0.0677 0.02318 0.01268 -0.0118 0.8444 0.8791
0.500 0.0925 0.02324 0.01275 -0.0118 0.8353 0.8903
0.750 0.1312 0.02325 0.01279 -0.0140 0.8292 0.8981
1.000 0.1602 0.02336 0.01294 -0.0149 0.8207 0.9089
1.250 0.1957 0.02340 0.01303 -0.0167 0.8143 0.9189
1.500 0.2312 0.02354 0.01324 -0.0188 0.8065 0.9284
1.750 0.2687 0.02362 0.01340 -0.0211 0.7998 0.9384
2.000 0.3044 0.02377 0.01368 -0.0233 0.7924 0.9493
2.250 0.3475 0.02387 0.01391 -0.0268 0.7852 0.9576
2.500 0.3881 0.02401 0.01422 -0.0299 0.7777 0.9673
2.750 0.4285 0.02409 0.01448 -0.0328 0.7693 0.9775
3.000 0.4674 0.02424 0.01482 -0.0357 0.7598 0.9888
3.250 0.5087 0.02423 0.01504 -0.0384 0.7518 1.0000
3.500 0.5162 0.02462 0.01554 -0.0357 0.7402 1.0000
3.750 0.5270 0.02489 0.01593 -0.0332 0.7290 1.0000
4.000 0.5426 0.02496 0.01612 -0.0309 0.7171 1.0000
4.250 0.5576 0.02485 0.01613 -0.0281 0.7004 1.0000
4.500 0.5805 0.02392 0.01532 -0.0248 0.6754 1.0000
4.750 0.5951 0.02301 0.01445 -0.0203 0.6380 1.0000
5.000 0.6100 0.02214 0.01354 -0.0160 0.5904 1.0000
5.250 0.6240 0.02175 0.01312 -0.0123 0.5323 1.0000
5.500 0.6369 0.02172 0.01291 -0.0088 0.4302 1.0000
5.750 0.6376 0.02324 0.01299 -0.0044 0.2390 1.0000
6.000 0.6397 0.02543 0.01443 -0.0019 0.1568 1.0000
6.250 0.6475 0.02721 0.01585 0.0000 0.1243 1.0000
6.500 0.6591 0.02870 0.01722 0.0017 0.1085 1.0000
6.750 0.6730 0.03009 0.01857 0.0032 0.0966 1.0000
7.000 0.6904 0.03136 0.01993 0.0044 0.0868 1.0000
7.250 0.7113 0.03280 0.02133 0.0054 0.0808 1.0000
7.500 0.7379 0.03410 0.02282 0.0059 0.0737 1.0000
7.750 0.7661 0.03574 0.02436 0.0059 0.0683 1.0000
8.000 0.7983 0.03760 0.02655 0.0059 0.0647 1.0000
8.250 0.8241 0.03949 0.02864 0.0062 0.0608 1.0000
8.500 0.8473 0.04156 0.03073 0.0063 0.0575 1.0000
8.750 0.8691 0.04419 0.03367 0.0068 0.0557 1.0000
9.000 0.8864 0.04705 0.03699 0.0077 0.0546 1.0000
9.250 0.8991 0.05011 0.04050 0.0088 0.0536 1.0000
9.500 0.9068 0.05323 0.04404 0.0100 0.0526 1.0000
9.750 0.9100 0.05637 0.04755 0.0114 0.0513 1.0000
10.000 0.9098 0.05948 0.05097 0.0128 0.0502 1.0000
10.250 0.9060 0.06270 0.05446 0.0141 0.0494 1.0000
10.500 0.8964 0.06593 0.05792 0.0156 0.0490 1.0000
10.750 0.8822 0.06953 0.06174 0.0165 0.0488 1.0000
11.000 0.8634 0.07378 0.06620 0.0164 0.0488 1.0000
11.250 0.8386 0.07910 0.07173 0.0147 0.0493 1.0000
11.500 0.8108 0.08570 0.07849 0.0114 0.0499 1.0000
11.750 0.7815 0.09392 0.08682 0.0061 0.0509 1.0000
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Polar data table (+)
Polar graphs
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