NACA 2408 (naca2408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2408 (naca2408-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.12 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2408-il-1000000-n5.txt Download as CSV file: xf-naca2408-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2408
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -1.0172 0.03854 0.03631 -0.0520 1.0000 0.0036
-12.250 -1.0198 0.03336 0.03079 -0.0536 1.0000 0.0036
-12.000 -1.0120 0.03012 0.02729 -0.0538 1.0000 0.0037
-11.750 -0.9992 0.02771 0.02465 -0.0537 1.0000 0.0037
-11.500 -0.9833 0.02584 0.02257 -0.0534 1.0000 0.0038
-11.250 -0.9654 0.02428 0.02083 -0.0530 1.0000 0.0039
-11.000 -0.9473 0.02276 0.01912 -0.0524 1.0000 0.0039
-10.750 -0.9304 0.02097 0.01711 -0.0518 1.0000 0.0041
-10.500 -0.9106 0.01978 0.01579 -0.0511 1.0000 0.0043
-10.250 -0.8900 0.01882 0.01469 -0.0503 1.0000 0.0045
-10.000 -0.8691 0.01795 0.01371 -0.0496 1.0000 0.0046
-9.750 -0.8478 0.01716 0.01281 -0.0487 1.0000 0.0048
-9.500 -0.8264 0.01641 0.01195 -0.0479 1.0000 0.0049
-9.250 -0.8049 0.01571 0.01114 -0.0470 1.0000 0.0051
-9.000 -0.7834 0.01505 0.01038 -0.0461 1.0000 0.0053
-8.750 -0.7599 0.01443 0.00966 -0.0455 0.9998 0.0055
-8.500 -0.7299 0.01382 0.00894 -0.0463 0.9985 0.0057
-8.250 -0.6998 0.01312 0.00812 -0.0471 0.9970 0.0060
-8.000 -0.6692 0.01248 0.00740 -0.0481 0.9956 0.0065
-7.750 -0.6382 0.01199 0.00686 -0.0490 0.9943 0.0070
-7.500 -0.6082 0.01156 0.00638 -0.0497 0.9923 0.0075
-7.250 -0.5773 0.01116 0.00591 -0.0505 0.9903 0.0080
-7.000 -0.5458 0.01073 0.00541 -0.0515 0.9884 0.0086
-6.750 -0.5140 0.01028 0.00492 -0.0525 0.9866 0.0097
-6.500 -0.4838 0.00993 0.00453 -0.0532 0.9830 0.0107
-6.250 -0.4530 0.00962 0.00417 -0.0539 0.9784 0.0117
-6.000 -0.4223 0.00928 0.00383 -0.0545 0.9736 0.0141
-5.750 -0.3931 0.00902 0.00358 -0.0549 0.9675 0.0166
-5.500 -0.3637 0.00878 0.00333 -0.0552 0.9620 0.0199
-5.250 -0.3355 0.00860 0.00316 -0.0553 0.9549 0.0231
-5.000 -0.3072 0.00847 0.00299 -0.0553 0.9477 0.0249
-4.750 -0.2795 0.00837 0.00286 -0.0552 0.9389 0.0256
-4.500 -0.2523 0.00813 0.00257 -0.0551 0.9298 0.0274
-4.250 -0.2251 0.00794 0.00234 -0.0548 0.9199 0.0296
-4.000 -0.1980 0.00779 0.00215 -0.0546 0.9086 0.0312
-3.750 -0.1708 0.00766 0.00198 -0.0544 0.8966 0.0329
-3.500 -0.1435 0.00755 0.00181 -0.0541 0.8840 0.0344
-3.250 -0.1162 0.00746 0.00165 -0.0539 0.8706 0.0353
-3.000 -0.0889 0.00734 0.00148 -0.0537 0.8562 0.0390
-2.750 -0.0616 0.00723 0.00134 -0.0535 0.8412 0.0435
-2.500 -0.0343 0.00714 0.00122 -0.0533 0.8252 0.0516
-2.250 -0.0071 0.00702 0.00111 -0.0532 0.8090 0.0703
-2.000 0.0203 0.00692 0.00102 -0.0530 0.7920 0.0893
-1.750 0.0477 0.00684 0.00094 -0.0529 0.7742 0.1097
-1.500 0.0750 0.00676 0.00087 -0.0528 0.7554 0.1333
-1.250 0.1023 0.00668 0.00082 -0.0527 0.7365 0.1622
-1.000 0.1297 0.00659 0.00078 -0.0526 0.7175 0.1978
-0.750 0.1570 0.00651 0.00075 -0.0525 0.6968 0.2362
-0.500 0.1843 0.00647 0.00073 -0.0524 0.6761 0.2733
-0.250 0.2115 0.00635 0.00072 -0.0524 0.6541 0.3306
0.000 0.2376 0.00627 0.00073 -0.0522 0.6143 0.4119
0.250 0.2632 0.00611 0.00076 -0.0519 0.5695 0.5311
0.500 0.2894 0.00599 0.00080 -0.0517 0.5379 0.6257
0.750 0.3148 0.00588 0.00086 -0.0513 0.5028 0.7266
1.000 0.3398 0.00580 0.00093 -0.0507 0.4718 0.8072
1.250 0.3634 0.00576 0.00100 -0.0496 0.4415 0.8813
1.500 0.3876 0.00583 0.00108 -0.0486 0.4065 0.9474
1.750 0.4219 0.00612 0.00117 -0.0501 0.3531 0.9837
2.000 0.4549 0.00649 0.00128 -0.0515 0.2935 1.0000
2.250 0.4795 0.00699 0.00146 -0.0510 0.2190 1.0000
2.500 0.5042 0.00748 0.00166 -0.0506 0.1522 1.0000
2.750 0.5295 0.00791 0.00186 -0.0503 0.0993 1.0000
3.000 0.5552 0.00828 0.00206 -0.0499 0.0614 1.0000
3.250 0.5813 0.00859 0.00225 -0.0497 0.0364 1.0000
3.500 0.6083 0.00876 0.00240 -0.0495 0.0343 1.0000
3.750 0.6352 0.00894 0.00257 -0.0493 0.0326 1.0000
4.000 0.6621 0.00912 0.00275 -0.0491 0.0312 1.0000
4.250 0.6889 0.00932 0.00295 -0.0490 0.0301 1.0000
4.500 0.7156 0.00953 0.00318 -0.0488 0.0290 1.0000
4.750 0.7422 0.00977 0.00345 -0.0485 0.0279 1.0000
5.000 0.7686 0.01002 0.00373 -0.0483 0.0269 1.0000
5.250 0.7953 0.01021 0.00393 -0.0481 0.0265 1.0000
5.500 0.8220 0.01041 0.00414 -0.0480 0.0258 1.0000
5.750 0.8484 0.01063 0.00438 -0.0478 0.0247 1.0000
6.000 0.8748 0.01087 0.00465 -0.0475 0.0234 1.0000
6.250 0.9009 0.01112 0.00491 -0.0473 0.0219 1.0000
6.500 0.9269 0.01141 0.00521 -0.0470 0.0205 1.0000
6.750 0.9522 0.01177 0.00559 -0.0467 0.0185 1.0000
7.000 0.9780 0.01205 0.00590 -0.0464 0.0175 1.0000
7.250 1.0040 0.01228 0.00616 -0.0462 0.0165 1.0000
7.500 1.0298 0.01254 0.00642 -0.0459 0.0146 1.0000
7.750 1.0549 0.01288 0.00671 -0.0456 0.0120 1.0000
8.000 1.0798 0.01325 0.00709 -0.0452 0.0105 1.0000
8.250 1.1042 0.01367 0.00750 -0.0448 0.0089 1.0000
8.500 1.1283 0.01413 0.00801 -0.0443 0.0079 1.0000
8.750 1.1523 0.01457 0.00851 -0.0438 0.0073 1.0000
9.000 1.1759 0.01506 0.00904 -0.0432 0.0067 1.0000
9.250 1.1990 0.01559 0.00961 -0.0426 0.0062 1.0000
9.500 1.2211 0.01624 0.01032 -0.0419 0.0056 1.0000
9.750 1.2436 0.01682 0.01096 -0.0412 0.0053 1.0000
10.000 1.2659 0.01738 0.01159 -0.0405 0.0051 1.0000
10.250 1.2878 0.01797 0.01225 -0.0397 0.0048 1.0000
10.500 1.3092 0.01859 0.01295 -0.0390 0.0045 1.0000
10.750 1.3299 0.01926 0.01369 -0.0381 0.0042 1.0000
11.000 1.3497 0.02002 0.01451 -0.0371 0.0040 1.0000
11.250 1.3678 0.02093 0.01551 -0.0359 0.0038 1.0000
11.500 1.3847 0.02192 0.01662 -0.0346 0.0036 1.0000
11.750 1.4024 0.02275 0.01754 -0.0334 0.0035 1.0000
12.000 1.4190 0.02364 0.01854 -0.0321 0.0034 1.0000
12.250 1.4342 0.02459 0.01960 -0.0306 0.0033 1.0000
12.500 1.4479 0.02561 0.02073 -0.0290 0.0032 1.0000
12.750 1.4587 0.02668 0.02193 -0.0269 0.0031 1.0000
13.000 1.4667 0.02780 0.02316 -0.0245 0.0030 1.0000
13.250 1.4730 0.02906 0.02454 -0.0221 0.0030 1.0000
13.500 1.4779 0.03046 0.02606 -0.0199 0.0029 1.0000
13.750 1.4818 0.03202 0.02774 -0.0179 0.0028 1.0000
14.000 1.4839 0.03382 0.02967 -0.0161 0.0028 1.0000
14.250 1.4852 0.03583 0.03181 -0.0147 0.0027 1.0000
14.500 1.4846 0.03818 0.03430 -0.0136 0.0027 1.0000
14.750 1.4822 0.04092 0.03717 -0.0130 0.0027 1.0000
15.000 1.4779 0.04412 0.04051 -0.0130 0.0026 1.0000
15.250 1.4712 0.04789 0.04443 -0.0136 0.0026 1.0000
15.500 1.4619 0.05234 0.04902 -0.0149 0.0026 1.0000
15.750 1.4503 0.05746 0.05430 -0.0169 0.0025 1.0000
16.000 1.4343 0.06366 0.06066 -0.0198 0.0025 1.0000
16.250 1.4144 0.07082 0.06799 -0.0235 0.0025 1.0000
16.500 1.3896 0.07925 0.07660 -0.0280 0.0025 1.0000
16.750 1.3596 0.08904 0.08656 -0.0332 0.0026 1.0000
17.000 1.3208 0.10116 0.09886 -0.0397 0.0026 1.0000
17.250 1.2695 0.11653 0.11444 -0.0478 0.0027 1.0000
17.500 1.2009 0.13670 0.13483 -0.0581 0.0028 1.0000
17.750 1.1109 0.16445 0.16279 -0.0729 0.0031 1.0000
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Polar data table (+)
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