NACA 2412 (naca2412-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2412 (naca2412-il) Reynolds number: 500,000 Max Cl/Cd: 87.28 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2412-il-500000.txt Download as CSV file: xf-naca2412-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8999 0.08481 0.08190 -0.0365 1.0000 0.0235
-15.000 -0.9520 0.07088 0.06775 -0.0463 1.0000 0.0232
-14.750 -0.9855 0.06054 0.05719 -0.0544 1.0000 0.0231
-14.500 -1.0072 0.05275 0.04918 -0.0609 1.0000 0.0232
-14.250 -1.0219 0.04686 0.04307 -0.0658 1.0000 0.0234
-14.000 -1.0318 0.04250 0.03849 -0.0688 1.0000 0.0237
-13.750 -1.0378 0.03941 0.03520 -0.0700 1.0000 0.0239
-13.500 -1.0497 0.03620 0.03177 -0.0694 1.0000 0.0242
-13.250 -1.0540 0.03399 0.02948 -0.0675 1.0000 0.0247
-13.000 -1.0488 0.03291 0.02838 -0.0656 1.0000 0.0252
-12.750 -1.0381 0.03207 0.02750 -0.0641 1.0000 0.0257
-12.500 -1.0273 0.03117 0.02652 -0.0626 1.0000 0.0264
-12.250 -1.0168 0.03019 0.02543 -0.0608 1.0000 0.0271
-12.000 -1.0065 0.02917 0.02426 -0.0589 1.0000 0.0278
-11.750 -0.9953 0.02829 0.02322 -0.0568 1.0000 0.0285
-11.500 -0.9869 0.02685 0.02159 -0.0545 1.0000 0.0291
-11.250 -0.9769 0.02537 0.02007 -0.0523 1.0000 0.0299
-11.000 -0.9620 0.02476 0.01944 -0.0505 1.0000 0.0307
-10.750 -0.9469 0.02420 0.01884 -0.0487 1.0000 0.0315
-10.500 -0.9318 0.02358 0.01813 -0.0467 1.0000 0.0324
-10.250 -0.9166 0.02293 0.01738 -0.0448 1.0000 0.0333
-10.000 -0.9007 0.02237 0.01668 -0.0429 1.0000 0.0340
-9.750 -0.8865 0.02130 0.01547 -0.0409 1.0000 0.0348
-9.500 -0.8719 0.02019 0.01434 -0.0390 1.0000 0.0359
-9.250 -0.8546 0.01966 0.01379 -0.0374 1.0000 0.0368
-9.000 -0.8367 0.01915 0.01325 -0.0358 1.0000 0.0378
-8.750 -0.8185 0.01864 0.01266 -0.0343 1.0000 0.0388
-8.500 -0.7877 0.01812 0.01206 -0.0353 0.9986 0.0400
-8.250 -0.7531 0.01769 0.01152 -0.0369 0.9966 0.0408
-8.000 -0.7217 0.01639 0.01017 -0.0383 0.9948 0.0424
-7.750 -0.6878 0.01581 0.00959 -0.0399 0.9928 0.0440
-7.500 -0.6543 0.01531 0.00904 -0.0413 0.9899 0.0454
-7.250 -0.6189 0.01480 0.00849 -0.0431 0.9873 0.0468
-7.000 -0.5811 0.01440 0.00801 -0.0453 0.9852 0.0482
-6.750 -0.5445 0.01360 0.00719 -0.0474 0.9832 0.0504
-6.500 -0.5126 0.01310 0.00669 -0.0484 0.9786 0.0525
-6.250 -0.4767 0.01269 0.00626 -0.0502 0.9759 0.0550
-6.000 -0.4394 0.01227 0.00580 -0.0522 0.9740 0.0582
-5.750 -0.4016 0.01177 0.00535 -0.0545 0.9725 0.0640
-5.500 -0.3704 0.01135 0.00495 -0.0552 0.9675 0.0715
-5.250 -0.3366 0.01094 0.00461 -0.0565 0.9637 0.0836
-5.000 -0.3017 0.01058 0.00430 -0.0580 0.9606 0.0980
-4.750 -0.2717 0.01028 0.00404 -0.0584 0.9549 0.1109
-4.500 -0.2416 0.00999 0.00379 -0.0588 0.9488 0.1241
-4.250 -0.2107 0.00969 0.00354 -0.0593 0.9438 0.1394
-4.000 -0.1846 0.00941 0.00333 -0.0588 0.9347 0.1573
-3.750 -0.1557 0.00913 0.00312 -0.0589 0.9283 0.1814
-3.500 -0.1299 0.00886 0.00295 -0.0583 0.9182 0.2093
-3.250 -0.1026 0.00860 0.00279 -0.0581 0.9096 0.2396
-3.000 -0.0758 0.00837 0.00265 -0.0577 0.8995 0.2712
-2.750 -0.0492 0.00815 0.00253 -0.0573 0.8888 0.3069
-2.500 -0.0223 0.00792 0.00240 -0.0570 0.8783 0.3436
-2.250 0.0042 0.00769 0.00228 -0.0566 0.8667 0.3827
-2.000 0.0306 0.00747 0.00219 -0.0562 0.8542 0.4278
-1.750 0.0569 0.00724 0.00211 -0.0558 0.8416 0.4810
-1.500 0.0830 0.00703 0.00205 -0.0553 0.8288 0.5417
-1.250 0.1092 0.00686 0.00200 -0.0547 0.8155 0.5954
-1.000 0.1353 0.00672 0.00197 -0.0541 0.8015 0.6434
-0.500 0.1867 0.00646 0.00195 -0.0527 0.7718 0.7418
-0.250 0.2118 0.00637 0.00197 -0.0518 0.7562 0.7912
0.000 0.2360 0.00630 0.00202 -0.0505 0.7403 0.8463
0.250 0.2601 0.00630 0.00208 -0.0491 0.7238 0.8941
0.500 0.2864 0.00637 0.00213 -0.0483 0.7067 0.9264
0.750 0.3169 0.00648 0.00217 -0.0485 0.6888 0.9475
1.000 0.3503 0.00661 0.00221 -0.0494 0.6701 0.9637
1.250 0.3860 0.00674 0.00226 -0.0509 0.6502 0.9757
1.500 0.4242 0.00688 0.00231 -0.0530 0.6294 0.9845
1.750 0.4653 0.00704 0.00235 -0.0558 0.6084 0.9908
2.000 0.5062 0.00720 0.00240 -0.0586 0.5888 0.9965
2.250 0.5424 0.00733 0.00246 -0.0605 0.5710 1.0000
2.500 0.5662 0.00744 0.00250 -0.0597 0.5553 1.0000
2.750 0.5899 0.00757 0.00256 -0.0589 0.5400 1.0000
3.000 0.6135 0.00771 0.00263 -0.0580 0.5230 1.0000
3.250 0.6371 0.00786 0.00270 -0.0572 0.5055 1.0000
3.500 0.6608 0.00801 0.00280 -0.0563 0.4892 1.0000
3.750 0.6846 0.00817 0.00290 -0.0555 0.4724 1.0000
4.000 0.7085 0.00833 0.00301 -0.0546 0.4553 1.0000
4.250 0.7321 0.00852 0.00313 -0.0538 0.4346 1.0000
4.500 0.7553 0.00875 0.00326 -0.0528 0.4121 1.0000
4.750 0.7791 0.00896 0.00340 -0.0520 0.3915 1.0000
5.000 0.8030 0.00920 0.00357 -0.0512 0.3692 1.0000
5.250 0.8265 0.00948 0.00375 -0.0504 0.3462 1.0000
5.500 0.8502 0.00978 0.00396 -0.0497 0.3204 1.0000
5.750 0.8734 0.01013 0.00420 -0.0489 0.2928 1.0000
6.000 0.8963 0.01053 0.00447 -0.0480 0.2639 1.0000
6.250 0.9188 0.01098 0.00477 -0.0472 0.2341 1.0000
6.500 0.9410 0.01147 0.00511 -0.0463 0.2038 1.0000
6.750 0.9628 0.01200 0.00550 -0.0453 0.1738 1.0000
7.000 0.9843 0.01257 0.00591 -0.0444 0.1443 1.0000
7.250 1.0051 0.01320 0.00637 -0.0433 0.1160 1.0000
7.500 1.0257 0.01383 0.00688 -0.0422 0.0954 1.0000
7.750 1.0464 0.01445 0.00742 -0.0411 0.0820 1.0000
8.000 1.0679 0.01498 0.00793 -0.0402 0.0732 1.0000
8.250 1.0884 0.01558 0.00851 -0.0390 0.0667 1.0000
8.500 1.1097 0.01609 0.00903 -0.0380 0.0624 1.0000
8.750 1.1276 0.01685 0.00978 -0.0365 0.0581 1.0000
9.000 1.1494 0.01727 0.01026 -0.0356 0.0559 1.0000
9.250 1.1699 0.01778 0.01080 -0.0345 0.0535 1.0000
9.500 1.1880 0.01843 0.01146 -0.0331 0.0512 1.0000
9.750 1.2022 0.01932 0.01239 -0.0312 0.0490 1.0000
10.000 1.2216 0.01981 0.01294 -0.0299 0.0477 1.0000
10.250 1.2383 0.02036 0.01354 -0.0283 0.0461 1.0000
10.500 1.2536 0.02096 0.01419 -0.0265 0.0446 1.0000
10.750 1.2666 0.02174 0.01499 -0.0245 0.0431 1.0000
11.000 1.2720 0.02305 0.01633 -0.0216 0.0415 1.0000
11.250 1.2875 0.02371 0.01709 -0.0201 0.0406 1.0000
11.500 1.3022 0.02444 0.01789 -0.0186 0.0394 1.0000
11.750 1.3157 0.02526 0.01878 -0.0171 0.0381 1.0000
12.000 1.3281 0.02618 0.01975 -0.0156 0.0369 1.0000
12.250 1.3363 0.02745 0.02104 -0.0139 0.0357 1.0000
12.500 1.3383 0.02930 0.02295 -0.0117 0.0345 1.0000
12.750 1.3516 0.03026 0.02403 -0.0107 0.0336 1.0000
13.000 1.3628 0.03143 0.02529 -0.0096 0.0325 1.0000
13.250 1.3727 0.03275 0.02667 -0.0086 0.0314 1.0000
13.500 1.3809 0.03426 0.02824 -0.0077 0.0305 1.0000
13.750 1.3838 0.03631 0.03033 -0.0067 0.0296 1.0000
14.000 1.3838 0.03874 0.03285 -0.0056 0.0287 1.0000
14.250 1.3917 0.04051 0.03475 -0.0052 0.0279 1.0000
14.500 1.3976 0.04251 0.03687 -0.0048 0.0270 1.0000
14.750 1.4025 0.04470 0.03914 -0.0047 0.0262 1.0000
15.000 1.4063 0.04706 0.04157 -0.0047 0.0254 1.0000
15.250 1.4070 0.04981 0.04438 -0.0049 0.0248 1.0000
15.500 1.3999 0.05341 0.04803 -0.0048 0.0241 1.0000
15.750 1.4008 0.05640 0.05116 -0.0053 0.0236 1.0000
16.000 1.4007 0.05959 0.05451 -0.0060 0.0230 1.0000
16.250 1.3992 0.06303 0.05807 -0.0068 0.0224 1.0000
16.500 1.3966 0.06670 0.06185 -0.0079 0.0219 1.0000
16.750 1.3936 0.07052 0.06576 -0.0091 0.0214 1.0000
17.000 1.3896 0.07453 0.06986 -0.0104 0.0210 1.0000
17.250 1.3842 0.07879 0.07421 -0.0119 0.0206 1.0000
17.500 1.3769 0.08337 0.07885 -0.0136 0.0203 1.0000
17.750 1.3662 0.08827 0.08382 -0.0150 0.0198 1.0000
18.000 1.3573 0.09332 0.08901 -0.0171 0.0196 1.0000
18.250 1.3482 0.09861 0.09446 -0.0194 0.0193 1.0000
18.500 1.3382 0.10412 0.10011 -0.0219 0.0190 1.0000
18.750 1.3276 0.10980 0.10593 -0.0245 0.0187 1.0000
19.000 1.3169 0.11559 0.11185 -0.0273 0.0184 1.0000
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