NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-34 (naca001234-il) Reynolds number: 200,000 Max Cl/Cd: 47.58 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001234-il-200000.txt Download as CSV file: xf-naca001234-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-34
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4678 0.11468 0.11123 -0.0286 1.0000 0.0538
-12.000 -0.4784 0.10942 0.10601 -0.0313 1.0000 0.0558
-11.750 -0.6288 0.10691 0.10338 -0.0279 1.0000 0.0476
-11.500 -0.6235 0.10455 0.10103 -0.0270 1.0000 0.0489
-11.250 -0.6264 0.09969 0.09618 -0.0291 1.0000 0.0501
-11.000 -0.6381 0.09188 0.08841 -0.0346 1.0000 0.0507
-10.750 -0.6685 0.08181 0.07828 -0.0430 1.0000 0.0498
-10.500 -0.6967 0.07567 0.07203 -0.0461 1.0000 0.0495
-10.250 -0.7190 0.07143 0.06770 -0.0462 1.0000 0.0496
-10.000 -0.7377 0.06813 0.06430 -0.0444 1.0000 0.0500
-9.750 -0.7560 0.06543 0.06152 -0.0411 1.0000 0.0505
-9.500 -0.7712 0.06285 0.05884 -0.0374 1.0000 0.0514
-9.250 -0.7841 0.06027 0.05612 -0.0335 1.0000 0.0527
-9.000 -0.7970 0.05793 0.05358 -0.0290 1.0000 0.0547
-7.000 -0.8047 0.03346 0.02620 0.0082 1.0000 0.0349
-6.750 -0.7855 0.03006 0.02263 0.0099 1.0000 0.0325
-6.500 -0.7678 0.02752 0.01979 0.0120 1.0000 0.0317
-6.250 -0.7479 0.02554 0.01754 0.0137 1.0000 0.0317
-6.000 -0.7271 0.02394 0.01576 0.0153 1.0000 0.0322
-5.750 -0.7080 0.02306 0.01472 0.0170 1.0000 0.0336
-5.500 -0.6879 0.02120 0.01279 0.0184 1.0000 0.0358
-5.250 -0.6712 0.01992 0.01152 0.0203 1.0000 0.0376
-5.000 -0.6556 0.01900 0.01058 0.0224 1.0000 0.0399
-4.750 -0.6399 0.01822 0.00973 0.0246 1.0000 0.0429
-4.500 -0.6248 0.01740 0.00886 0.0267 1.0000 0.0481
-4.250 -0.6085 0.01670 0.00811 0.0285 1.0000 0.0563
-4.000 -0.5923 0.01573 0.00726 0.0305 1.0000 0.0845
-3.750 -0.5916 0.01256 0.00638 0.0340 1.0000 0.4942
-3.500 -0.5652 0.01188 0.00646 0.0343 0.9969 0.6595
-3.250 -0.5327 0.01191 0.00676 0.0338 0.9935 0.7474
-3.000 -0.5028 0.01217 0.00716 0.0341 0.9887 0.8056
-2.750 -0.4701 0.01267 0.00767 0.0340 0.9845 0.8454
-2.500 -0.4370 0.01306 0.00798 0.0334 0.9800 0.8655
-2.250 -0.4027 0.01332 0.00815 0.0323 0.9748 0.8791
-2.000 -0.3631 0.01365 0.00839 0.0300 0.9711 0.8910
-1.750 -0.3274 0.01392 0.00857 0.0284 0.9663 0.9022
-1.500 -0.2911 0.01414 0.00870 0.0267 0.9609 0.9125
-1.250 -0.2435 0.01443 0.00891 0.0226 0.9581 0.9178
-1.000 -0.1944 0.01466 0.00907 0.0181 0.9558 0.9237
-0.750 -0.1563 0.01480 0.00916 0.0158 0.9495 0.9303
-0.500 -0.1042 0.01495 0.00927 0.0106 0.9465 0.9335
-0.250 -0.0510 0.01502 0.00931 0.0051 0.9440 0.9371
0.000 0.0000 0.01499 0.00927 0.0000 0.9418 0.9418
0.250 0.0511 0.01502 0.00931 -0.0051 0.9371 0.9440
0.500 0.1042 0.01495 0.00927 -0.0106 0.9335 0.9465
0.750 0.1563 0.01480 0.00916 -0.0158 0.9303 0.9495
1.000 0.1945 0.01466 0.00907 -0.0181 0.9237 0.9559
1.250 0.2435 0.01443 0.00891 -0.0226 0.9178 0.9581
1.500 0.2910 0.01414 0.00869 -0.0267 0.9125 0.9609
1.750 0.3274 0.01392 0.00857 -0.0284 0.9022 0.9663
2.000 0.3631 0.01365 0.00838 -0.0300 0.8911 0.9711
2.250 0.4027 0.01332 0.00815 -0.0323 0.8791 0.9748
2.500 0.4370 0.01305 0.00797 -0.0334 0.8655 0.9800
2.750 0.4702 0.01267 0.00767 -0.0340 0.8455 0.9846
3.000 0.5028 0.01217 0.00716 -0.0341 0.8056 0.9887
3.250 0.5327 0.01190 0.00675 -0.0338 0.7471 0.9936
3.500 0.5652 0.01188 0.00646 -0.0343 0.6596 0.9969
3.750 0.5915 0.01255 0.00638 -0.0340 0.4945 1.0000
4.000 0.5923 0.01571 0.00725 -0.0305 0.0853 1.0000
4.250 0.6083 0.01669 0.00811 -0.0285 0.0563 1.0000
4.500 0.6247 0.01739 0.00885 -0.0267 0.0482 1.0000
4.750 0.6398 0.01821 0.00972 -0.0246 0.0430 1.0000
5.000 0.6555 0.01899 0.01057 -0.0224 0.0400 1.0000
5.250 0.6711 0.01991 0.01151 -0.0203 0.0377 1.0000
5.500 0.6877 0.02119 0.01278 -0.0184 0.0359 1.0000
5.750 0.7079 0.02304 0.01470 -0.0170 0.0336 1.0000
6.000 0.7270 0.02394 0.01576 -0.0153 0.0322 1.0000
6.250 0.7477 0.02553 0.01753 -0.0137 0.0317 1.0000
6.500 0.7677 0.02750 0.01978 -0.0120 0.0318 1.0000
6.750 0.7854 0.03005 0.02262 -0.0099 0.0325 1.0000
7.000 0.8046 0.03346 0.02620 -0.0082 0.0349 1.0000
12.000 0.4781 0.10924 0.10583 0.0313 0.0558 1.0000
12.250 0.4673 0.11450 0.11105 0.0286 0.0538 1.0000
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Polar data table (+)
Polar graphs
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