NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-015A AIRFOIL (n63015a-il) Reynolds number: 50,000 Max Cl/Cd: 28.49 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63015a-il-50000-n5.txt Download as CSV file: xf-n63015a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-015A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7540 0.10804 0.10026 -0.0228 1.0000 0.0564
-13.750 -0.7819 0.09892 0.09103 -0.0281 1.0000 0.0561
-13.500 -0.8098 0.09088 0.08283 -0.0326 1.0000 0.0558
-13.250 -0.8356 0.08396 0.07572 -0.0360 1.0000 0.0557
-13.000 -0.8586 0.07801 0.06954 -0.0383 1.0000 0.0556
-12.750 -0.8783 0.07286 0.06414 -0.0396 1.0000 0.0557
-12.500 -0.8946 0.06833 0.05933 -0.0401 1.0000 0.0559
-12.250 -0.9072 0.06432 0.05500 -0.0399 1.0000 0.0562
-12.000 -0.9147 0.06077 0.05116 -0.0392 1.0000 0.0568
-11.750 -0.9067 0.05824 0.04859 -0.0386 1.0000 0.0582
-11.500 -0.9013 0.05587 0.04611 -0.0378 1.0000 0.0599
-11.250 -0.8964 0.05345 0.04350 -0.0368 1.0000 0.0619
-11.000 -0.8892 0.05099 0.04075 -0.0357 1.0000 0.0642
-10.750 -0.8777 0.04856 0.03792 -0.0347 1.0000 0.0666
-10.500 -0.8558 0.04667 0.03609 -0.0343 1.0000 0.0697
-10.250 -0.8393 0.04497 0.03428 -0.0335 1.0000 0.0739
-10.000 -0.8177 0.04325 0.03232 -0.0328 1.0000 0.0791
-9.750 -0.7985 0.04179 0.03091 -0.0320 1.0000 0.0845
-9.500 -0.7789 0.04036 0.02932 -0.0311 1.0000 0.0920
-9.250 -0.7646 0.03891 0.02794 -0.0299 1.0000 0.0994
-9.000 -0.7521 0.03745 0.02647 -0.0284 1.0000 0.1085
-8.750 -0.7416 0.03599 0.02499 -0.0268 1.0000 0.1196
-8.500 -0.7344 0.03451 0.02357 -0.0248 1.0000 0.1328
-8.250 -0.7304 0.03301 0.02220 -0.0224 1.0000 0.1478
-8.000 -0.7291 0.03151 0.02089 -0.0195 1.0000 0.1660
-7.750 -0.7273 0.03003 0.01960 -0.0166 1.0000 0.1915
-7.500 -0.7279 0.02855 0.01844 -0.0133 1.0000 0.2249
-7.250 -0.7296 0.02718 0.01749 -0.0095 1.0000 0.2702
-7.000 -0.7305 0.02614 0.01692 -0.0053 1.0000 0.3285
-6.750 -0.7272 0.02559 0.01675 -0.0012 1.0000 0.3902
-6.500 -0.7216 0.02533 0.01663 0.0027 1.0000 0.4398
-6.250 -0.7134 0.02529 0.01666 0.0064 1.0000 0.4782
-6.000 -0.7047 0.02531 0.01666 0.0100 1.0000 0.5096
-5.750 -0.6968 0.02529 0.01656 0.0135 1.0000 0.5367
-5.500 -0.6846 0.02553 0.01677 0.0167 1.0000 0.5600
-5.250 -0.6755 0.02559 0.01675 0.0200 1.0000 0.5826
-5.000 -0.6624 0.02587 0.01697 0.0230 1.0000 0.6027
-4.750 -0.6457 0.02618 0.01721 0.0254 0.9990 0.6218
-4.500 -0.6081 0.02662 0.01749 0.0239 0.9897 0.6425
-4.250 -0.5709 0.02689 0.01760 0.0223 0.9804 0.6600
-4.000 -0.5323 0.02709 0.01762 0.0204 0.9717 0.6744
-3.750 -0.4958 0.02713 0.01751 0.0186 0.9621 0.6871
-3.500 -0.4619 0.02700 0.01721 0.0170 0.9520 0.6996
-3.250 -0.4207 0.02699 0.01705 0.0143 0.9446 0.7100
-3.000 -0.3870 0.02691 0.01685 0.0129 0.9343 0.7192
-2.750 -0.3526 0.02665 0.01644 0.0109 0.9253 0.7305
-2.500 -0.3139 0.02669 0.01639 0.0089 0.9168 0.7378
-2.250 -0.2829 0.02646 0.01606 0.0077 0.9071 0.7481
-2.000 -0.2449 0.02645 0.01596 0.0058 0.8988 0.7556
-1.750 -0.2167 0.02627 0.01571 0.0052 0.8887 0.7655
-1.500 -0.1787 0.02623 0.01560 0.0033 0.8810 0.7731
-1.250 -0.1528 0.02611 0.01544 0.0033 0.8705 0.7827
-1.000 -0.1151 0.02605 0.01533 0.0015 0.8634 0.7905
-0.750 -0.0907 0.02600 0.01525 0.0017 0.8524 0.7999
-0.500 -0.0561 0.02595 0.01516 0.0005 0.8449 0.8081
-0.250 -0.0298 0.02594 0.01515 0.0005 0.8347 0.8171
0.000 0.0000 0.02592 0.01512 0.0000 0.8262 0.8262
0.250 0.0298 0.02594 0.01515 -0.0005 0.8171 0.8347
0.500 0.0561 0.02595 0.01516 -0.0005 0.8081 0.8450
0.750 0.0907 0.02600 0.01525 -0.0017 0.7998 0.8524
1.000 0.1151 0.02605 0.01533 -0.0015 0.7905 0.8634
1.250 0.1528 0.02611 0.01544 -0.0033 0.7827 0.8705
1.500 0.1788 0.02623 0.01560 -0.0033 0.7731 0.8810
1.750 0.2167 0.02627 0.01571 -0.0052 0.7655 0.8888
2.000 0.2449 0.02644 0.01596 -0.0058 0.7557 0.8989
2.250 0.2829 0.02646 0.01606 -0.0077 0.7481 0.9072
2.500 0.3139 0.02669 0.01639 -0.0089 0.7378 0.9168
2.750 0.3526 0.02665 0.01644 -0.0109 0.7305 0.9254
3.000 0.3871 0.02691 0.01685 -0.0129 0.7192 0.9343
3.250 0.4207 0.02699 0.01704 -0.0143 0.7100 0.9446
3.500 0.4619 0.02700 0.01721 -0.0170 0.6996 0.9521
3.750 0.4958 0.02712 0.01750 -0.0186 0.6871 0.9621
4.000 0.5323 0.02708 0.01762 -0.0204 0.6744 0.9717
4.250 0.5709 0.02689 0.01760 -0.0223 0.6600 0.9804
4.500 0.6082 0.02662 0.01749 -0.0239 0.6425 0.9897
4.750 0.6458 0.02618 0.01720 -0.0254 0.6218 0.9990
5.000 0.6623 0.02586 0.01697 -0.0230 0.6027 1.0000
5.250 0.6754 0.02559 0.01674 -0.0200 0.5827 1.0000
5.500 0.6845 0.02553 0.01677 -0.0167 0.5601 1.0000
5.750 0.6968 0.02529 0.01656 -0.0135 0.5367 1.0000
6.000 0.7046 0.02530 0.01665 -0.0100 0.5096 1.0000
6.250 0.7133 0.02529 0.01665 -0.0064 0.4782 1.0000
6.500 0.7216 0.02533 0.01663 -0.0027 0.4398 1.0000
6.750 0.7272 0.02559 0.01674 0.0012 0.3902 1.0000
7.000 0.7305 0.02613 0.01692 0.0053 0.3285 1.0000
7.250 0.7296 0.02718 0.01748 0.0095 0.2701 1.0000
7.500 0.7279 0.02855 0.01844 0.0133 0.2248 1.0000
7.750 0.7274 0.03003 0.01960 0.0166 0.1914 1.0000
8.000 0.7292 0.03151 0.02089 0.0195 0.1660 1.0000
8.250 0.7306 0.03301 0.02220 0.0224 0.1478 1.0000
8.500 0.7346 0.03451 0.02357 0.0248 0.1328 1.0000
8.750 0.7419 0.03599 0.02499 0.0267 0.1196 1.0000
9.000 0.7525 0.03744 0.02647 0.0284 0.1085 1.0000
9.250 0.7651 0.03891 0.02793 0.0298 0.0993 1.0000
9.500 0.7794 0.04036 0.02932 0.0310 0.0919 1.0000
9.750 0.7990 0.04179 0.03091 0.0319 0.0844 1.0000
10.000 0.8184 0.04325 0.03231 0.0327 0.0790 1.0000
10.250 0.8399 0.04497 0.03428 0.0334 0.0739 1.0000
10.500 0.8564 0.04667 0.03609 0.0342 0.0697 1.0000
10.750 0.8783 0.04857 0.03793 0.0346 0.0666 1.0000
11.000 0.8898 0.05100 0.04076 0.0357 0.0642 1.0000
11.250 0.8970 0.05346 0.04351 0.0367 0.0619 1.0000
11.500 0.9020 0.05588 0.04612 0.0377 0.0598 1.0000
11.750 0.9075 0.05825 0.04859 0.0385 0.0581 1.0000
12.000 0.9156 0.06078 0.05117 0.0391 0.0568 1.0000
12.250 0.9078 0.06435 0.05503 0.0398 0.0562 1.0000
12.500 0.8952 0.06838 0.05937 0.0399 0.0559 1.0000
12.750 0.8790 0.07291 0.06419 0.0394 0.0557 1.0000
13.000 0.8593 0.07807 0.06961 0.0381 0.0556 1.0000
13.250 0.8362 0.08404 0.07581 0.0358 0.0556 1.0000
13.500 0.8104 0.09099 0.08294 0.0324 0.0558 1.0000
13.750 0.7826 0.09905 0.09116 0.0279 0.0561 1.0000
14.000 0.7546 0.10823 0.10044 0.0225 0.0564 1.0000
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