NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)-215 MOD B (n63215b-il) Reynolds number: 50,000 Max Cl/Cd: 24.53 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63215b-il-50000-n5.txt Download as CSV file: xf-n63215b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-215 MOD B
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5757 0.10346 0.09565 -0.0283 1.0000 0.0652
-12.500 -0.6228 0.08968 0.08177 -0.0374 1.0000 0.0640
-12.250 -0.6778 0.07796 0.06982 -0.0454 1.0000 0.0626
-12.000 -0.7140 0.07081 0.06242 -0.0493 1.0000 0.0621
-11.750 -0.7353 0.06596 0.05736 -0.0509 1.0000 0.0622
-11.500 -0.7492 0.06209 0.05330 -0.0514 1.0000 0.0626
-11.250 -0.7582 0.05882 0.04986 -0.0512 1.0000 0.0632
-11.000 -0.7645 0.05599 0.04686 -0.0504 1.0000 0.0643
-10.750 -0.7696 0.05344 0.04412 -0.0491 1.0000 0.0656
-10.500 -0.7726 0.05101 0.04145 -0.0474 1.0000 0.0671
-10.250 -0.7714 0.04856 0.03868 -0.0459 1.0000 0.0688
-10.000 -0.7622 0.04625 0.03615 -0.0446 1.0000 0.0704
-9.500 -0.7278 0.04276 0.03260 -0.0429 1.0000 0.0749
-9.250 -0.7128 0.04119 0.03088 -0.0416 1.0000 0.0783
-9.000 -0.6956 0.03966 0.02908 -0.0403 1.0000 0.0815
-8.750 -0.6716 0.03830 0.02790 -0.0395 1.0000 0.0848
-8.500 -0.6529 0.03718 0.02678 -0.0381 1.0000 0.0886
-8.250 -0.6367 0.03619 0.02563 -0.0364 1.0000 0.0937
-8.000 -0.6257 0.03524 0.02481 -0.0341 1.0000 0.0981
-7.750 -0.6193 0.03442 0.02403 -0.0312 1.0000 0.1029
-7.500 -0.6151 0.03370 0.02324 -0.0279 1.0000 0.1080
-7.250 -0.6177 0.03293 0.02259 -0.0241 1.0000 0.1126
-7.000 -0.6195 0.03221 0.02189 -0.0203 1.0000 0.1189
-6.750 -0.6210 0.03141 0.02114 -0.0167 1.0000 0.1264
-6.500 -0.6150 0.03044 0.02021 -0.0145 0.9978 0.1387
-6.250 -0.5921 0.02885 0.01886 -0.0159 0.9875 0.1651
-6.000 -0.5706 0.02709 0.01756 -0.0173 0.9780 0.2153
-5.750 -0.5520 0.02557 0.01682 -0.0178 0.9682 0.3088
-5.500 -0.5287 0.02528 0.01707 -0.0172 0.9595 0.4115
-5.250 -0.4980 0.02564 0.01753 -0.0174 0.9524 0.4803
-5.000 -0.4733 0.02613 0.01797 -0.0164 0.9437 0.5231
-4.750 -0.4409 0.02677 0.01852 -0.0164 0.9375 0.5575
-4.500 -0.4155 0.02745 0.01914 -0.0148 0.9297 0.5800
-4.250 -0.3826 0.02812 0.01972 -0.0145 0.9238 0.6016
-4.000 -0.3562 0.02860 0.02010 -0.0135 0.9169 0.6211
-3.750 -0.3276 0.02900 0.02040 -0.0129 0.9104 0.6375
-3.500 -0.2918 0.02928 0.02056 -0.0137 0.9060 0.6502
-3.250 -0.2727 0.02924 0.02042 -0.0124 0.8975 0.6613
-3.000 -0.2431 0.02912 0.02016 -0.0131 0.8918 0.6738
-2.750 -0.2178 0.02932 0.02031 -0.0122 0.8853 0.6815
-2.500 -0.1940 0.02919 0.02007 -0.0120 0.8784 0.6921
-2.250 -0.1604 0.02924 0.02004 -0.0128 0.8738 0.6999
-2.000 -0.1445 0.02916 0.01989 -0.0114 0.8653 0.7094
-1.750 -0.1128 0.02917 0.01984 -0.0119 0.8593 0.7173
-1.500 -0.0901 0.02907 0.01968 -0.0113 0.8497 0.7264
-1.250 -0.0504 0.02890 0.01944 -0.0127 0.8411 0.7340
-1.000 -0.0266 0.02869 0.01917 -0.0119 0.8281 0.7427
-0.750 0.0020 0.02852 0.01897 -0.0114 0.8156 0.7501
-0.500 0.0336 0.02821 0.01860 -0.0116 0.8045 0.7587
-0.250 0.0643 0.02799 0.01836 -0.0113 0.7929 0.7660
0.000 0.0886 0.02770 0.01804 -0.0102 0.7786 0.7752
0.250 0.1157 0.02740 0.01773 -0.0091 0.7637 0.7830
0.500 0.1409 0.02705 0.01737 -0.0080 0.7491 0.7921
0.750 0.1672 0.02675 0.01708 -0.0068 0.7351 0.8002
1.000 0.1927 0.02640 0.01672 -0.0057 0.7205 0.8091
1.250 0.2181 0.02604 0.01638 -0.0044 0.7044 0.8176
1.500 0.2417 0.02566 0.01601 -0.0029 0.6859 0.8266
1.750 0.2650 0.02526 0.01563 -0.0012 0.6655 0.8362
2.000 0.2907 0.02478 0.01514 0.0003 0.6427 0.8450
2.250 0.3105 0.02443 0.01481 0.0023 0.6143 0.8562
2.500 0.3341 0.02405 0.01443 0.0039 0.5794 0.8659
2.750 0.3565 0.02374 0.01404 0.0056 0.5355 0.8766
3.000 0.3796 0.02351 0.01359 0.0072 0.4822 0.8883
3.250 0.4056 0.02353 0.01321 0.0082 0.4286 0.8988
3.500 0.4295 0.02387 0.01313 0.0090 0.3912 0.9101
3.750 0.4545 0.02437 0.01330 0.0091 0.3654 0.9223
4.000 0.4828 0.02497 0.01367 0.0086 0.3446 0.9347
4.250 0.5175 0.02562 0.01418 0.0068 0.3259 0.9455
4.500 0.5543 0.02627 0.01474 0.0046 0.3098 0.9569
4.750 0.5923 0.02692 0.01532 0.0021 0.2951 0.9689
5.000 0.6318 0.02758 0.01592 -0.0006 0.2819 0.9813
5.250 0.6726 0.02826 0.01652 -0.0037 0.2706 0.9945
5.500 0.6896 0.02877 0.01709 -0.0027 0.2621 1.0000
5.750 0.7020 0.02926 0.01748 -0.0007 0.2553 1.0000
6.000 0.7180 0.02987 0.01812 0.0005 0.2475 1.0000
6.250 0.7383 0.03051 0.01870 0.0011 0.2398 1.0000
6.500 0.7605 0.03130 0.01949 0.0014 0.2326 1.0000
6.750 0.7829 0.03209 0.02030 0.0016 0.2253 1.0000
7.000 0.8074 0.03292 0.02104 0.0016 0.2193 1.0000
7.250 0.8293 0.03397 0.02224 0.0018 0.2129 1.0000
7.500 0.8537 0.03494 0.02320 0.0017 0.2077 1.0000
7.750 0.8780 0.03602 0.02426 0.0017 0.2031 1.0000
8.000 0.8962 0.03733 0.02580 0.0022 0.1972 1.0000
8.250 0.9176 0.03837 0.02686 0.0025 0.1921 1.0000
8.500 0.9404 0.03945 0.02789 0.0026 0.1877 1.0000
8.750 0.9529 0.04115 0.02991 0.0035 0.1827 1.0000
9.000 0.9695 0.04270 0.03160 0.0040 0.1788 1.0000
9.250 0.9897 0.04398 0.03290 0.0043 0.1753 1.0000
9.500 1.0081 0.04544 0.03438 0.0047 0.1720 1.0000
9.750 1.0083 0.04785 0.03717 0.0063 0.1682 1.0000
10.000 1.0113 0.04998 0.03951 0.0076 0.1646 1.0000
10.250 1.0206 0.05163 0.04125 0.0086 0.1613 1.0000
10.500 1.0385 0.05291 0.04252 0.0089 0.1586 1.0000
10.750 1.0373 0.05534 0.04509 0.0104 0.1566 1.0000
11.000 1.0058 0.05958 0.04968 0.0125 0.1550 1.0000
11.250 0.9599 0.06574 0.05615 0.0127 0.1537 1.0000
11.500 0.8130 0.08747 0.07833 0.0021 0.1526 1.0000
11.750 0.7412 0.10586 0.09681 -0.0090 0.1482 1.0000
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Polar data table (+)
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