N-12 (n12-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-12 (n12-il) Reynolds number: 200,000 Max Cl/Cd: 46.45 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n12-il-200000.txt Download as CSV file: xf-n12-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: N-12
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.8601 0.04001 0.03429 -0.0142 1.0000 0.0607
-8.250 -0.8562 0.03472 0.02836 -0.0100 1.0000 0.0523
-8.000 -0.8510 0.03122 0.02400 -0.0053 1.0000 0.0482
-7.750 -0.8348 0.02956 0.02203 -0.0031 1.0000 0.0477
-7.500 -0.8175 0.02712 0.01938 -0.0014 1.0000 0.0483
-7.250 -0.7982 0.02519 0.01734 0.0000 1.0000 0.0495
-7.000 -0.7777 0.02367 0.01565 0.0015 1.0000 0.0499
-6.750 -0.7567 0.02230 0.01417 0.0029 1.0000 0.0505
-6.500 -0.7359 0.02114 0.01293 0.0043 1.0000 0.0513
-6.250 -0.7160 0.02014 0.01189 0.0058 1.0000 0.0528
-6.000 -0.6965 0.01923 0.01093 0.0075 1.0000 0.0541
-5.750 -0.6778 0.01838 0.01002 0.0093 1.0000 0.0549
-5.500 -0.6600 0.01762 0.00923 0.0113 1.0000 0.0557
-5.250 -0.6429 0.01696 0.00853 0.0134 1.0000 0.0566
-5.000 -0.6266 0.01635 0.00788 0.0156 1.0000 0.0580
-4.750 -0.6121 0.01566 0.00718 0.0181 1.0000 0.0601
-4.500 -0.5962 0.01517 0.00667 0.0204 1.0000 0.0620
-4.250 -0.5795 0.01478 0.00625 0.0225 1.0000 0.0644
-4.000 -0.5623 0.01447 0.00590 0.0245 1.0000 0.0672
-3.750 -0.5454 0.01414 0.00561 0.0266 1.0000 0.0734
-3.500 -0.5290 0.01376 0.00542 0.0286 1.0000 0.1018
-3.250 -0.5130 0.01336 0.00521 0.0306 1.0000 0.1427
-3.000 -0.4977 0.01291 0.00501 0.0327 1.0000 0.1942
-2.750 -0.4854 0.01225 0.00489 0.0352 1.0000 0.2993
-2.500 -0.4708 0.01193 0.00487 0.0374 1.0000 0.3813
-2.250 -0.4336 0.01169 0.00494 0.0350 0.9944 0.4527
-2.000 -0.4027 0.01118 0.00501 0.0341 0.9873 0.5623
-1.750 -0.3707 0.01081 0.00520 0.0334 0.9803 0.6882
-1.500 -0.3287 0.01064 0.00537 0.0310 0.9732 0.7742
-1.250 -0.2828 0.01053 0.00545 0.0280 0.9646 0.8429
-1.000 -0.2227 0.01056 0.00555 0.0222 0.9596 0.8889
-0.750 -0.1498 0.01090 0.00592 0.0140 0.9584 0.9226
-0.500 -0.0897 0.01107 0.00606 0.0082 0.9512 0.9350
-0.250 -0.0331 0.01111 0.00606 0.0029 0.9454 0.9433
0.000 0.0212 0.01111 0.00605 -0.0020 0.9366 0.9482
0.250 0.0803 0.01108 0.00601 -0.0080 0.9283 0.9543
0.500 0.1384 0.01102 0.00596 -0.0139 0.9182 0.9596
0.750 0.1998 0.01087 0.00581 -0.0206 0.9031 0.9614
1.000 0.2575 0.01075 0.00567 -0.0266 0.8791 0.9631
1.250 0.3060 0.01073 0.00560 -0.0307 0.8482 0.9669
1.500 0.3464 0.01077 0.00557 -0.0330 0.8126 0.9727
1.750 0.3888 0.01078 0.00545 -0.0357 0.7650 0.9784
2.000 0.4246 0.01088 0.00530 -0.0369 0.6958 0.9852
2.250 0.4607 0.01101 0.00511 -0.0385 0.6232 0.9916
2.500 0.4961 0.01119 0.00496 -0.0402 0.5450 0.9978
2.750 0.5189 0.01141 0.00491 -0.0394 0.4792 1.0000
3.000 0.5334 0.01170 0.00494 -0.0370 0.4227 1.0000
3.250 0.5482 0.01202 0.00501 -0.0348 0.3713 1.0000
3.500 0.5644 0.01230 0.00514 -0.0327 0.3362 1.0000
3.750 0.5814 0.01256 0.00530 -0.0308 0.3062 1.0000
4.000 0.5978 0.01287 0.00548 -0.0288 0.2672 1.0000
4.250 0.6103 0.01358 0.00566 -0.0262 0.1463 1.0000
4.500 0.6197 0.01477 0.00646 -0.0230 0.0936 1.0000
4.750 0.6352 0.01530 0.00697 -0.0207 0.0809 1.0000
5.000 0.6517 0.01572 0.00739 -0.0185 0.0741 1.0000
5.250 0.6662 0.01633 0.00798 -0.0160 0.0698 1.0000
5.500 0.6823 0.01682 0.00851 -0.0138 0.0659 1.0000
5.750 0.6981 0.01737 0.00906 -0.0115 0.0625 1.0000
6.000 0.7119 0.01835 0.01000 -0.0090 0.0599 1.0000
6.250 0.7288 0.01919 0.01088 -0.0068 0.0584 1.0000
6.500 0.7469 0.01994 0.01170 -0.0049 0.0561 1.0000
6.750 0.7651 0.02075 0.01257 -0.0031 0.0536 1.0000
7.000 0.7838 0.02176 0.01362 -0.0014 0.0519 1.0000
7.250 0.8031 0.02306 0.01494 0.0001 0.0503 1.0000
7.500 0.8227 0.02530 0.01728 0.0014 0.0485 1.0000
7.750 0.8403 0.02625 0.01847 0.0034 0.0471 1.0000
8.000 0.8577 0.02788 0.02034 0.0053 0.0461 1.0000
8.250 0.8733 0.02974 0.02249 0.0075 0.0452 1.0000
8.500 0.8871 0.03151 0.02451 0.0099 0.0440 1.0000
8.750 0.9000 0.03328 0.02647 0.0121 0.0427 1.0000
9.000 0.9132 0.03511 0.02843 0.0142 0.0416 1.0000
9.250 0.9146 0.03844 0.03228 0.0181 0.0422 1.0000
9.500 0.9049 0.04328 0.03772 0.0231 0.0440 1.0000
9.750 0.8951 0.04787 0.04269 0.0272 0.0460 1.0000
10.000 0.8873 0.05200 0.04703 0.0304 0.0473 1.0000
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Polar data table (+)
Polar graphs
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