N-12 (n12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-12 (n12-il) Reynolds number: 100,000 Max Cl/Cd: 36.11 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n12-il-100000-n5.txt Download as CSV file: xf-n12-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7561 0.07847 0.07287 -0.0354 1.0000 0.0320
-11.750 -0.7982 0.06986 0.06401 -0.0417 1.0000 0.0313
-11.500 -0.8221 0.06523 0.05917 -0.0428 1.0000 0.0312
-11.250 -0.8426 0.06155 0.05530 -0.0421 1.0000 0.0311
-11.000 -0.8598 0.05820 0.05180 -0.0399 1.0000 0.0314
-10.750 -0.8752 0.05550 0.04891 -0.0366 1.0000 0.0315
-10.500 -0.8844 0.05282 0.04607 -0.0335 1.0000 0.0319
-10.250 -0.8877 0.05032 0.04340 -0.0309 1.0000 0.0326
-10.000 -0.8856 0.04816 0.04112 -0.0285 1.0000 0.0336
-9.750 -0.8847 0.04591 0.03866 -0.0258 1.0000 0.0346
-9.500 -0.8833 0.04347 0.03592 -0.0229 1.0000 0.0355
-9.250 -0.8793 0.04104 0.03315 -0.0201 1.0000 0.0363
-9.000 -0.8719 0.03875 0.03052 -0.0175 1.0000 0.0369
-8.750 -0.8620 0.03681 0.02822 -0.0150 1.0000 0.0381
-8.500 -0.8502 0.03528 0.02632 -0.0126 1.0000 0.0394
-8.250 -0.8361 0.03341 0.02415 -0.0106 1.0000 0.0405
-8.000 -0.8183 0.03107 0.02164 -0.0093 1.0000 0.0415
-7.750 -0.8000 0.02936 0.01985 -0.0080 1.0000 0.0427
-7.500 -0.7820 0.02800 0.01842 -0.0065 1.0000 0.0446
-7.250 -0.7635 0.02679 0.01710 -0.0050 1.0000 0.0464
-7.000 -0.7445 0.02564 0.01584 -0.0034 1.0000 0.0475
-6.750 -0.7260 0.02459 0.01469 -0.0018 1.0000 0.0485
-6.500 -0.7080 0.02365 0.01364 0.0000 1.0000 0.0494
-6.250 -0.6902 0.02287 0.01274 0.0018 1.0000 0.0510
-6.000 -0.6752 0.02188 0.01175 0.0040 1.0000 0.0527
-5.750 -0.6597 0.02104 0.01088 0.0062 1.0000 0.0545
-5.500 -0.6432 0.02036 0.01013 0.0082 1.0000 0.0560
-5.250 -0.6260 0.01976 0.00943 0.0102 1.0000 0.0575
-5.000 -0.6083 0.01922 0.00882 0.0121 1.0000 0.0593
-4.750 -0.5905 0.01873 0.00825 0.0139 1.0000 0.0617
-4.500 -0.5728 0.01822 0.00777 0.0158 1.0000 0.0658
-4.250 -0.5557 0.01768 0.00737 0.0177 1.0000 0.0765
-4.000 -0.5381 0.01721 0.00704 0.0195 1.0000 0.1147
-3.750 -0.5206 0.01677 0.00671 0.0213 1.0000 0.1436
-3.500 -0.5034 0.01632 0.00641 0.0231 1.0000 0.1761
-3.250 -0.4862 0.01591 0.00615 0.0249 1.0000 0.2124
-3.000 -0.4706 0.01540 0.00600 0.0269 1.0000 0.2788
-2.750 -0.4549 0.01499 0.00592 0.0289 1.0000 0.3628
-2.500 -0.4287 0.01478 0.00580 0.0289 0.9971 0.4058
-2.250 -0.3943 0.01449 0.00570 0.0272 0.9903 0.4558
-2.000 -0.3639 0.01388 0.00580 0.0265 0.9836 0.5794
-1.750 -0.3305 0.01357 0.00599 0.0258 0.9772 0.6982
-1.500 -0.2895 0.01356 0.00629 0.0240 0.9727 0.7863
-1.250 -0.2460 0.01373 0.00658 0.0216 0.9677 0.8518
-1.000 -0.1965 0.01392 0.00676 0.0177 0.9635 0.8839
-0.750 -0.1447 0.01403 0.00684 0.0133 0.9544 0.9058
-0.500 -0.0891 0.01405 0.00681 0.0081 0.9417 0.9199
-0.250 -0.0306 0.01397 0.00667 0.0023 0.9271 0.9266
0.000 0.0223 0.01387 0.00653 -0.0024 0.9113 0.9335
0.250 0.0754 0.01381 0.00643 -0.0074 0.8968 0.9381
0.500 0.1248 0.01375 0.00636 -0.0116 0.8816 0.9435
0.750 0.1709 0.01370 0.00629 -0.0152 0.8626 0.9499
1.000 0.2198 0.01366 0.00623 -0.0192 0.8355 0.9555
1.250 0.2636 0.01367 0.00620 -0.0221 0.8018 0.9636
1.500 0.3064 0.01367 0.00615 -0.0249 0.7621 0.9705
1.750 0.3463 0.01371 0.00610 -0.0271 0.7172 0.9774
2.000 0.3843 0.01380 0.00607 -0.0290 0.6710 0.9847
2.250 0.4240 0.01388 0.00600 -0.0313 0.6199 0.9911
2.500 0.4615 0.01403 0.00598 -0.0333 0.5676 0.9980
2.750 0.4852 0.01426 0.00601 -0.0326 0.5125 1.0000
3.000 0.5015 0.01456 0.00606 -0.0304 0.4535 1.0000
3.250 0.5174 0.01491 0.00616 -0.0282 0.4000 1.0000
3.500 0.5334 0.01529 0.00630 -0.0261 0.3546 1.0000
3.750 0.5505 0.01563 0.00650 -0.0242 0.3210 1.0000
4.000 0.5678 0.01597 0.00674 -0.0224 0.2909 1.0000
4.250 0.5852 0.01631 0.00702 -0.0205 0.2577 1.0000
4.500 0.6026 0.01669 0.00732 -0.0187 0.2194 1.0000
4.750 0.6161 0.01748 0.00763 -0.0164 0.1327 1.0000
5.000 0.6294 0.01845 0.00835 -0.0140 0.1043 1.0000
5.250 0.6456 0.01911 0.00906 -0.0119 0.0864 1.0000
5.500 0.6621 0.01974 0.00970 -0.0098 0.0770 1.0000
5.750 0.6787 0.02034 0.01036 -0.0078 0.0708 1.0000
6.000 0.6942 0.02106 0.01106 -0.0056 0.0669 1.0000
6.250 0.7102 0.02175 0.01186 -0.0034 0.0636 1.0000
6.500 0.7263 0.02245 0.01264 -0.0014 0.0601 1.0000
6.750 0.7414 0.02325 0.01343 0.0007 0.0570 1.0000
7.000 0.7562 0.02425 0.01445 0.0030 0.0549 1.0000
7.250 0.7729 0.02522 0.01555 0.0050 0.0532 1.0000
7.500 0.7900 0.02625 0.01668 0.0068 0.0509 1.0000
7.750 0.8068 0.02726 0.01775 0.0085 0.0482 1.0000
8.000 0.8234 0.02846 0.01898 0.0102 0.0461 1.0000
8.250 0.8410 0.03029 0.02085 0.0116 0.0444 1.0000
8.500 0.8577 0.03163 0.02248 0.0134 0.0426 1.0000
8.750 0.8727 0.03307 0.02417 0.0153 0.0403 1.0000
9.000 0.8870 0.03479 0.02612 0.0173 0.0388 1.0000
9.250 0.8991 0.03658 0.02812 0.0193 0.0375 1.0000
9.500 0.9100 0.03830 0.02998 0.0213 0.0360 1.0000
9.750 0.9184 0.04097 0.03275 0.0232 0.0346 1.0000
10.000 0.9194 0.04296 0.03517 0.0266 0.0335 1.0000
10.250 0.9179 0.04546 0.03806 0.0298 0.0328 1.0000
10.500 0.9115 0.04823 0.04118 0.0333 0.0322 1.0000
10.750 0.8996 0.05102 0.04427 0.0370 0.0318 1.0000
11.000 0.8832 0.05373 0.04722 0.0408 0.0315 1.0000
11.250 0.8654 0.05678 0.05050 0.0433 0.0312 1.0000
11.500 0.8439 0.06071 0.05464 0.0443 0.0313 1.0000
11.750 0.8209 0.06538 0.05950 0.0434 0.0314 1.0000
12.000 0.7954 0.07135 0.06566 0.0403 0.0317 1.0000
12.250 0.7653 0.07953 0.07398 0.0347 0.0321 1.0000
12.500 0.7308 0.09072 0.08526 0.0266 0.0326 1.0000
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Polar data table (+)
Polar graphs
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