NACA 63-412 AIRFOIL (n63412-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-412 AIRFOIL (n63412-il) Reynolds number: 200,000 Max Cl/Cd: 70.59 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63412-il-200000-n5.txt Download as CSV file: xf-n63412-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-412 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5922 0.06654 0.06268 -0.0567 1.0000 0.0176
-11.000 -0.6185 0.05869 0.05470 -0.0629 1.0000 0.0176
-10.750 -0.6387 0.05337 0.04925 -0.0664 1.0000 0.0175
-10.500 -0.6626 0.04883 0.04454 -0.0678 1.0000 0.0175
-10.250 -0.6859 0.04557 0.04111 -0.0665 1.0000 0.0175
-10.000 -0.7050 0.04177 0.03699 -0.0647 1.0000 0.0176
-9.750 -0.7158 0.03843 0.03329 -0.0625 1.0000 0.0178
-9.500 -0.7160 0.03625 0.03096 -0.0604 1.0000 0.0180
-9.250 -0.7064 0.03457 0.02915 -0.0595 0.9983 0.0184
-9.000 -0.6795 0.03247 0.02681 -0.0618 0.9912 0.0190
-8.750 -0.6503 0.03076 0.02489 -0.0642 0.9852 0.0201
-8.500 -0.6232 0.02850 0.02223 -0.0659 0.9777 0.0213
-8.250 -0.5942 0.02623 0.01947 -0.0675 0.9714 0.0224
-8.000 -0.5650 0.02427 0.01728 -0.0689 0.9649 0.0232
-7.750 -0.5349 0.02305 0.01598 -0.0703 0.9581 0.0241
-7.500 -0.5035 0.02210 0.01492 -0.0718 0.9514 0.0255
-7.250 -0.4725 0.02108 0.01370 -0.0729 0.9445 0.0272
-7.000 -0.4418 0.02000 0.01244 -0.0739 0.9370 0.0284
-6.750 -0.4122 0.01882 0.01117 -0.0747 0.9295 0.0295
-6.500 -0.3830 0.01800 0.01034 -0.0755 0.9209 0.0313
-6.250 -0.3545 0.01734 0.00960 -0.0760 0.9118 0.0334
-6.000 -0.3259 0.01664 0.00880 -0.0764 0.9033 0.0353
-5.750 -0.2995 0.01603 0.00809 -0.0763 0.8936 0.0369
-5.500 -0.2731 0.01528 0.00731 -0.0765 0.8852 0.0397
-5.250 -0.2468 0.01483 0.00680 -0.0765 0.8759 0.0433
-5.000 -0.2200 0.01439 0.00626 -0.0764 0.8677 0.0467
-4.750 -0.1937 0.01387 0.00571 -0.0764 0.8592 0.0521
-4.500 -0.1670 0.01347 0.00526 -0.0764 0.8511 0.0603
-4.250 -0.1402 0.01303 0.00483 -0.0764 0.8430 0.0753
-4.000 -0.1138 0.01252 0.00446 -0.0765 0.8350 0.1122
-3.750 -0.0878 0.01177 0.00405 -0.0768 0.8273 0.2014
-3.500 -0.0625 0.01089 0.00375 -0.0771 0.8195 0.3463
-3.250 -0.0360 0.01049 0.00365 -0.0771 0.8119 0.4466
-3.000 -0.0089 0.01033 0.00360 -0.0769 0.8044 0.5004
-2.750 0.0183 0.01025 0.00359 -0.0767 0.7970 0.5456
-2.500 0.0455 0.01022 0.00360 -0.0764 0.7897 0.5836
-2.250 0.0725 0.01020 0.00360 -0.0760 0.7820 0.6103
-2.000 0.1000 0.01022 0.00359 -0.0757 0.7749 0.6315
-1.750 0.1275 0.01022 0.00357 -0.0755 0.7672 0.6441
-1.500 0.1553 0.01023 0.00353 -0.0754 0.7602 0.6549
-1.250 0.1832 0.01024 0.00349 -0.0753 0.7523 0.6653
-1.000 0.2112 0.01025 0.00346 -0.0752 0.7455 0.6748
-0.750 0.2389 0.01026 0.00345 -0.0751 0.7375 0.6836
-0.500 0.2672 0.01029 0.00341 -0.0751 0.7308 0.6934
-0.250 0.2946 0.01030 0.00343 -0.0750 0.7227 0.7012
0.000 0.3227 0.01034 0.00341 -0.0749 0.7161 0.7103
0.250 0.3501 0.01036 0.00346 -0.0748 0.7080 0.7184
0.500 0.3780 0.01040 0.00347 -0.0747 0.7013 0.7272
0.750 0.4054 0.01043 0.00354 -0.0746 0.6932 0.7357
1.000 0.4330 0.01048 0.00357 -0.0744 0.6864 0.7441
1.250 0.4605 0.01053 0.00366 -0.0743 0.6783 0.7531
1.500 0.4877 0.01058 0.00371 -0.0741 0.6714 0.7613
1.750 0.5152 0.01064 0.00382 -0.0740 0.6632 0.7707
2.000 0.5420 0.01070 0.00390 -0.0736 0.6560 0.7789
2.250 0.5693 0.01077 0.00402 -0.0735 0.6475 0.7882
2.500 0.5959 0.01084 0.00412 -0.0731 0.6400 0.7969
2.750 0.6226 0.01091 0.00426 -0.0728 0.6309 0.8060
3.000 0.6491 0.01100 0.00437 -0.0725 0.6226 0.8156
3.250 0.6749 0.01107 0.00452 -0.0720 0.6125 0.8246
3.500 0.7010 0.01115 0.00465 -0.0715 0.6008 0.8347
3.750 0.7261 0.01123 0.00477 -0.0708 0.5873 0.8448
4.000 0.7506 0.01131 0.00489 -0.0701 0.5709 0.8550
4.250 0.7749 0.01141 0.00500 -0.0692 0.5526 0.8663
4.750 0.8202 0.01171 0.00523 -0.0669 0.4968 0.8916
5.000 0.8410 0.01193 0.00537 -0.0655 0.4590 0.9069
5.250 0.8612 0.01220 0.00555 -0.0640 0.4164 0.9258
5.500 0.8827 0.01269 0.00582 -0.0631 0.3565 0.9584
5.750 0.9022 0.01365 0.00637 -0.0624 0.2750 1.0000
6.000 0.9187 0.01482 0.00710 -0.0613 0.1962 1.0000
6.250 0.9358 0.01594 0.00787 -0.0603 0.1347 1.0000
6.500 0.9536 0.01697 0.00863 -0.0593 0.0915 1.0000
6.750 0.9724 0.01788 0.00939 -0.0583 0.0661 1.0000
7.000 0.9919 0.01869 0.01013 -0.0574 0.0526 1.0000
7.250 1.0110 0.01948 0.01090 -0.0564 0.0446 1.0000
7.500 1.0306 0.02020 0.01168 -0.0555 0.0394 1.0000
7.750 1.0476 0.02108 0.01255 -0.0543 0.0353 1.0000
8.000 1.0644 0.02193 0.01349 -0.0529 0.0328 1.0000
8.250 1.0800 0.02277 0.01441 -0.0514 0.0306 1.0000
8.500 1.0930 0.02368 0.01537 -0.0496 0.0288 1.0000
8.750 1.1019 0.02488 0.01659 -0.0473 0.0272 1.0000
9.000 1.1143 0.02590 0.01770 -0.0456 0.0260 1.0000
9.250 1.1268 0.02695 0.01885 -0.0440 0.0246 1.0000
9.500 1.1387 0.02808 0.02006 -0.0424 0.0235 1.0000
9.750 1.1498 0.02932 0.02136 -0.0409 0.0227 1.0000
10.000 1.1604 0.03066 0.02276 -0.0395 0.0220 1.0000
10.250 1.1699 0.03218 0.02433 -0.0381 0.0214 1.0000
10.500 1.1798 0.03390 0.02609 -0.0367 0.0208 1.0000
10.750 1.1923 0.03538 0.02772 -0.0356 0.0204 1.0000
11.000 1.2047 0.03697 0.02945 -0.0345 0.0199 1.0000
11.250 1.2168 0.03866 0.03129 -0.0334 0.0195 1.0000
11.500 1.2281 0.04043 0.03321 -0.0324 0.0190 1.0000
11.750 1.2381 0.04228 0.03521 -0.0315 0.0185 1.0000
12.000 1.2465 0.04415 0.03723 -0.0306 0.0180 1.0000
12.250 1.2536 0.04614 0.03935 -0.0298 0.0176 1.0000
12.500 1.2594 0.04821 0.04155 -0.0292 0.0171 1.0000
12.750 1.2644 0.05049 0.04395 -0.0286 0.0168 1.0000
13.000 1.2684 0.05302 0.04661 -0.0281 0.0166 1.0000
13.250 1.2708 0.05589 0.04961 -0.0277 0.0164 1.0000
13.500 1.2700 0.05924 0.05315 -0.0274 0.0162 1.0000
13.750 1.2651 0.06291 0.05708 -0.0274 0.0160 1.0000
14.000 1.2577 0.06701 0.06145 -0.0279 0.0159 1.0000
14.250 1.2476 0.07160 0.06630 -0.0287 0.0158 1.0000
14.500 1.2353 0.07669 0.07165 -0.0301 0.0158 1.0000
14.750 1.2206 0.08236 0.07757 -0.0321 0.0157 1.0000
15.000 1.2039 0.08874 0.08420 -0.0349 0.0156 1.0000
15.250 1.1855 0.09582 0.09152 -0.0384 0.0156 1.0000
15.500 1.1654 0.10373 0.09966 -0.0428 0.0156 1.0000
15.750 1.1439 0.11253 0.10868 -0.0481 0.0156 1.0000
16.000 1.1203 0.12262 0.11898 -0.0546 0.0157 1.0000
16.250 1.0940 0.13428 0.13082 -0.0624 0.0158 1.0000
16.500 1.0626 0.14877 0.14548 -0.0720 0.0160 1.0000
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