NACA 1412 (naca1412-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1412 (naca1412-il) Reynolds number: 200,000 Max Cl/Cd: 53.29 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1412-il-200000-n5.txt Download as CSV file: xf-naca1412-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9052 0.09560 0.09129 -0.0205 1.0000 0.0266
-15.000 -0.9476 0.08305 0.07853 -0.0289 1.0000 0.0264
-14.750 -0.9791 0.07316 0.06841 -0.0358 1.0000 0.0264
-14.500 -1.0040 0.06502 0.06003 -0.0416 1.0000 0.0265
-14.250 -1.0237 0.05830 0.05304 -0.0462 1.0000 0.0267
-14.000 -1.0379 0.05304 0.04755 -0.0494 1.0000 0.0269
-13.750 -1.0419 0.04962 0.04404 -0.0508 1.0000 0.0273
-13.500 -1.0432 0.04679 0.04113 -0.0517 1.0000 0.0277
-13.250 -1.0434 0.04436 0.03861 -0.0520 1.0000 0.0281
-13.000 -1.0435 0.04216 0.03629 -0.0518 1.0000 0.0286
-12.750 -1.0433 0.04015 0.03413 -0.0509 1.0000 0.0292
-12.500 -1.0429 0.03830 0.03210 -0.0494 1.0000 0.0299
-12.250 -1.0419 0.03658 0.03019 -0.0473 1.0000 0.0306
-12.000 -1.0383 0.03497 0.02834 -0.0452 1.0000 0.0314
-11.750 -1.0305 0.03348 0.02657 -0.0434 1.0000 0.0322
-11.500 -1.0192 0.03208 0.02515 -0.0419 1.0000 0.0330
-11.250 -1.0055 0.03106 0.02409 -0.0406 1.0000 0.0339
-11.000 -0.9910 0.03006 0.02299 -0.0392 1.0000 0.0348
-10.750 -0.9759 0.02902 0.02182 -0.0378 1.0000 0.0359
-10.500 -0.9601 0.02798 0.02063 -0.0364 1.0000 0.0370
-10.250 -0.9435 0.02702 0.01947 -0.0350 1.0000 0.0382
-10.000 -0.9274 0.02592 0.01831 -0.0336 1.0000 0.0392
-9.750 -0.9106 0.02504 0.01739 -0.0322 1.0000 0.0402
-9.500 -0.8931 0.02427 0.01657 -0.0308 1.0000 0.0414
-9.250 -0.8753 0.02353 0.01576 -0.0293 1.0000 0.0427
-9.000 -0.8573 0.02281 0.01494 -0.0278 1.0000 0.0441
-8.750 -0.8389 0.02211 0.01412 -0.0263 1.0000 0.0453
-8.500 -0.8215 0.02130 0.01326 -0.0247 1.0000 0.0464
-8.250 -0.8040 0.02058 0.01254 -0.0231 1.0000 0.0479
-8.000 -0.7855 0.02000 0.01193 -0.0217 1.0000 0.0495
-7.750 -0.7667 0.01944 0.01132 -0.0202 1.0000 0.0512
-7.500 -0.7479 0.01889 0.01069 -0.0186 1.0000 0.0529
-7.250 -0.7289 0.01836 0.01010 -0.0171 1.0000 0.0545
-7.000 -0.7106 0.01776 0.00952 -0.0156 1.0000 0.0567
-6.750 -0.6911 0.01730 0.00905 -0.0143 1.0000 0.0596
-6.500 -0.6711 0.01690 0.00858 -0.0129 1.0000 0.0629
-6.250 -0.6477 0.01640 0.00810 -0.0124 0.9991 0.0669
-6.000 -0.6132 0.01593 0.00761 -0.0141 0.9955 0.0732
-5.750 -0.5790 0.01545 0.00714 -0.0157 0.9917 0.0814
-5.500 -0.5449 0.01501 0.00674 -0.0173 0.9872 0.0928
-5.250 -0.5089 0.01459 0.00637 -0.0193 0.9836 0.1076
-5.000 -0.4763 0.01420 0.00603 -0.0205 0.9779 0.1238
-4.750 -0.4407 0.01383 0.00571 -0.0224 0.9735 0.1426
-4.500 -0.4072 0.01346 0.00543 -0.0237 0.9681 0.1638
-4.250 -0.3732 0.01310 0.00516 -0.0252 0.9624 0.1896
-4.000 -0.3384 0.01271 0.00491 -0.0268 0.9577 0.2222
-3.750 -0.3088 0.01233 0.00470 -0.0273 0.9493 0.2585
-3.500 -0.2746 0.01196 0.00448 -0.0288 0.9438 0.2973
-3.250 -0.2463 0.01166 0.00430 -0.0288 0.9338 0.3290
-3.000 -0.2142 0.01136 0.00411 -0.0297 0.9264 0.3630
-2.750 -0.1854 0.01108 0.00395 -0.0298 0.9160 0.3969
-2.500 -0.1563 0.01081 0.00380 -0.0299 0.9058 0.4338
-2.250 -0.1265 0.01051 0.00366 -0.0301 0.8961 0.4752
-2.000 -0.0996 0.01026 0.00355 -0.0297 0.8835 0.5173
-1.750 -0.0724 0.01003 0.00346 -0.0293 0.8708 0.5601
-1.500 -0.0452 0.00982 0.00338 -0.0288 0.8575 0.6006
-1.250 -0.0184 0.00964 0.00331 -0.0283 0.8434 0.6390
-1.000 0.0083 0.00949 0.00325 -0.0276 0.8284 0.6759
-0.750 0.0346 0.00937 0.00321 -0.0268 0.8124 0.7122
-0.500 0.0607 0.00928 0.00319 -0.0259 0.7955 0.7471
-0.250 0.0868 0.00923 0.00319 -0.0250 0.7777 0.7805
0.000 0.1132 0.00922 0.00320 -0.0241 0.7591 0.8117
0.250 0.1403 0.00924 0.00323 -0.0234 0.7397 0.8401
0.500 0.1684 0.00931 0.00326 -0.0229 0.7199 0.8657
0.750 0.1978 0.00941 0.00330 -0.0227 0.6999 0.8885
1.000 0.2279 0.00951 0.00335 -0.0228 0.6794 0.9087
1.250 0.2593 0.00964 0.00340 -0.0232 0.6585 0.9260
1.500 0.2924 0.00979 0.00346 -0.0240 0.6373 0.9407
1.750 0.3268 0.00994 0.00353 -0.0251 0.6150 0.9536
2.000 0.3617 0.01011 0.00360 -0.0264 0.5912 0.9650
2.250 0.3971 0.01029 0.00367 -0.0279 0.5672 0.9749
2.500 0.4335 0.01047 0.00376 -0.0297 0.5434 0.9836
2.750 0.4719 0.01065 0.00384 -0.0320 0.5197 0.9904
3.000 0.5094 0.01083 0.00393 -0.0341 0.4940 0.9969
3.250 0.5393 0.01103 0.00403 -0.0347 0.4681 1.0000
3.500 0.5614 0.01123 0.00413 -0.0337 0.4437 1.0000
3.750 0.5836 0.01143 0.00426 -0.0326 0.4210 1.0000
4.000 0.6058 0.01165 0.00440 -0.0315 0.3979 1.0000
4.250 0.6277 0.01191 0.00456 -0.0304 0.3745 1.0000
4.500 0.6492 0.01220 0.00475 -0.0293 0.3460 1.0000
4.750 0.6698 0.01257 0.00496 -0.0280 0.3104 1.0000
5.000 0.6901 0.01300 0.00520 -0.0267 0.2723 1.0000
5.250 0.7105 0.01344 0.00548 -0.0255 0.2397 1.0000
5.500 0.7314 0.01387 0.00579 -0.0243 0.2127 1.0000
5.750 0.7521 0.01433 0.00613 -0.0231 0.1872 1.0000
6.000 0.7732 0.01480 0.00649 -0.0220 0.1635 1.0000
6.250 0.7940 0.01530 0.00690 -0.0209 0.1426 1.0000
6.500 0.8154 0.01578 0.00732 -0.0198 0.1246 1.0000
6.750 0.8367 0.01629 0.00777 -0.0188 0.1088 1.0000
7.000 0.8578 0.01682 0.00825 -0.0178 0.0954 1.0000
7.250 0.8787 0.01739 0.00878 -0.0167 0.0840 1.0000
7.500 0.8991 0.01800 0.00935 -0.0156 0.0747 1.0000
7.750 0.9200 0.01857 0.00993 -0.0145 0.0674 1.0000
8.000 0.9401 0.01920 0.01056 -0.0134 0.0624 1.0000
8.250 0.9604 0.01980 0.01122 -0.0123 0.0585 1.0000
8.500 0.9793 0.02052 0.01194 -0.0110 0.0555 1.0000
8.750 0.9980 0.02123 0.01269 -0.0097 0.0532 1.0000
9.000 1.0171 0.02190 0.01344 -0.0085 0.0509 1.0000
9.250 1.0354 0.02261 0.01421 -0.0072 0.0489 1.0000
9.500 1.0521 0.02343 0.01505 -0.0058 0.0472 1.0000
9.750 1.0666 0.02442 0.01605 -0.0041 0.0458 1.0000
10.000 1.0833 0.02523 0.01697 -0.0027 0.0447 1.0000
10.250 1.0990 0.02608 0.01792 -0.0011 0.0434 1.0000
10.500 1.1128 0.02695 0.01888 0.0006 0.0422 1.0000
10.750 1.1254 0.02785 0.01985 0.0025 0.0410 1.0000
11.000 1.1370 0.02885 0.02091 0.0043 0.0400 1.0000
11.250 1.1471 0.03004 0.02212 0.0062 0.0391 1.0000
11.500 1.1569 0.03136 0.02349 0.0079 0.0382 1.0000
11.750 1.1683 0.03251 0.02482 0.0094 0.0373 1.0000
12.000 1.1785 0.03379 0.02623 0.0109 0.0363 1.0000
12.250 1.1876 0.03516 0.02772 0.0122 0.0354 1.0000
12.500 1.1959 0.03662 0.02929 0.0135 0.0346 1.0000
12.750 1.2032 0.03817 0.03093 0.0146 0.0338 1.0000
13.000 1.2095 0.03987 0.03268 0.0155 0.0330 1.0000
13.250 1.2145 0.04181 0.03467 0.0163 0.0323 1.0000
13.500 1.2184 0.04395 0.03696 0.0171 0.0317 1.0000
13.750 1.2209 0.04627 0.03950 0.0175 0.0311 1.0000
14.000 1.2220 0.04882 0.04224 0.0177 0.0304 1.0000
14.250 1.2219 0.05160 0.04519 0.0176 0.0298 1.0000
14.500 1.2208 0.05457 0.04832 0.0172 0.0291 1.0000
14.750 1.2189 0.05772 0.05161 0.0165 0.0286 1.0000
15.000 1.2164 0.06107 0.05508 0.0156 0.0281 1.0000
15.250 1.2133 0.06457 0.05868 0.0144 0.0276 1.0000
15.500 1.2095 0.06825 0.06245 0.0131 0.0273 1.0000
15.750 1.2048 0.07214 0.06642 0.0118 0.0269 1.0000
16.000 1.1966 0.07670 0.07111 0.0100 0.0265 1.0000
16.250 1.1819 0.08265 0.07730 0.0070 0.0263 1.0000
16.500 1.1651 0.08927 0.08416 0.0034 0.0261 1.0000
16.750 1.1456 0.09664 0.09175 -0.0007 0.0259 1.0000
17.000 1.1229 0.10502 0.10034 -0.0056 0.0257 1.0000
17.250 1.0951 0.11487 0.11041 -0.0115 0.0256 1.0000
17.500 1.0571 0.12763 0.12342 -0.0194 0.0257 1.0000
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