NACA 2408 (naca2408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2408 (naca2408-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.81 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2408-il-1000000.txt Download as CSV file: xf-naca2408-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.8523 0.03757 0.03547 -0.0512 1.0000 0.0059
-10.500 -0.8601 0.03067 0.02806 -0.0529 1.0000 0.0060
-10.250 -0.8550 0.02660 0.02360 -0.0526 1.0000 0.0062
-10.000 -0.8389 0.02485 0.02170 -0.0520 1.0000 0.0064
-9.750 -0.8199 0.02379 0.02054 -0.0513 1.0000 0.0067
-9.500 -0.8012 0.02264 0.01925 -0.0505 1.0000 0.0069
-9.250 -0.7832 0.02130 0.01774 -0.0495 1.0000 0.0072
-9.000 -0.7655 0.01988 0.01613 -0.0483 1.0000 0.0074
-8.750 -0.7471 0.01859 0.01465 -0.0471 1.0000 0.0077
-8.500 -0.7280 0.01749 0.01337 -0.0458 1.0000 0.0079
-8.250 -0.7080 0.01660 0.01231 -0.0446 1.0000 0.0081
-8.000 -0.6871 0.01595 0.01154 -0.0435 1.0000 0.0083
-7.750 -0.6705 0.01379 0.00905 -0.0420 1.0000 0.0090
-7.500 -0.6492 0.01309 0.00828 -0.0409 1.0000 0.0095
-7.250 -0.6271 0.01262 0.00775 -0.0400 1.0000 0.0101
-7.000 -0.5952 0.01217 0.00723 -0.0411 0.9990 0.0108
-6.750 -0.5616 0.01178 0.00679 -0.0425 0.9977 0.0116
-6.500 -0.5285 0.01080 0.00564 -0.0438 0.9963 0.0130
-6.250 -0.4933 0.01035 0.00517 -0.0456 0.9950 0.0149
-6.000 -0.4591 0.01008 0.00488 -0.0470 0.9931 0.0166
-5.750 -0.4258 0.00958 0.00433 -0.0483 0.9909 0.0196
-5.500 -0.3914 0.00944 0.00424 -0.0498 0.9891 0.0233
-5.250 -0.3562 0.00942 0.00421 -0.0514 0.9876 0.0254
-5.000 -0.3216 0.00891 0.00366 -0.0530 0.9864 0.0296
-4.750 -0.2881 0.00874 0.00351 -0.0543 0.9841 0.0327
-4.500 -0.2559 0.00859 0.00332 -0.0552 0.9808 0.0346
-4.250 -0.2227 0.00847 0.00320 -0.0564 0.9779 0.0356
-4.000 -0.1916 0.00800 0.00266 -0.0571 0.9741 0.0382
-3.750 -0.1628 0.00774 0.00238 -0.0572 0.9680 0.0406
-3.500 -0.1331 0.00752 0.00214 -0.0575 0.9628 0.0429
-3.250 -0.1060 0.00734 0.00194 -0.0572 0.9547 0.0449
-3.000 -0.0784 0.00715 0.00171 -0.0570 0.9469 0.0498
-2.750 -0.0517 0.00686 0.00151 -0.0566 0.9380 0.0720
-2.500 -0.0252 0.00658 0.00137 -0.0563 0.9278 0.1135
-2.250 0.0015 0.00635 0.00125 -0.0560 0.9175 0.1515
-2.000 0.0283 0.00615 0.00115 -0.0557 0.9063 0.1909
-1.750 0.0551 0.00597 0.00106 -0.0555 0.8938 0.2335
-1.500 0.0819 0.00579 0.00099 -0.0552 0.8803 0.2814
-1.250 0.1087 0.00560 0.00093 -0.0550 0.8661 0.3386
-1.000 0.1353 0.00534 0.00088 -0.0548 0.8511 0.4206
-0.750 0.1615 0.00502 0.00085 -0.0545 0.8347 0.5331
-0.500 0.1875 0.00475 0.00084 -0.0541 0.8171 0.6366
-0.250 0.2123 0.00444 0.00085 -0.0534 0.7982 0.7563
0.000 0.2341 0.00419 0.00088 -0.0517 0.7707 0.8732
0.250 0.2592 0.00417 0.00090 -0.0505 0.7361 0.9644
0.500 0.2995 0.00430 0.00090 -0.0532 0.7022 0.9932
0.750 0.3336 0.00448 0.00090 -0.0546 0.6632 1.0000
1.000 0.3593 0.00464 0.00092 -0.0541 0.6308 1.0000
1.250 0.3851 0.00481 0.00095 -0.0537 0.5973 1.0000
1.500 0.4108 0.00501 0.00099 -0.0532 0.5619 1.0000
1.750 0.4368 0.00521 0.00105 -0.0529 0.5279 1.0000
2.000 0.4629 0.00541 0.00112 -0.0525 0.4945 1.0000
2.250 0.4888 0.00566 0.00119 -0.0522 0.4544 1.0000
2.500 0.5148 0.00593 0.00129 -0.0518 0.4117 1.0000
2.750 0.5404 0.00625 0.00141 -0.0515 0.3624 1.0000
3.000 0.5646 0.00680 0.00160 -0.0510 0.2804 1.0000
3.250 0.5883 0.00746 0.00187 -0.0505 0.1907 1.0000
3.500 0.6121 0.00813 0.00218 -0.0499 0.1091 1.0000
3.750 0.6370 0.00865 0.00246 -0.0495 0.0586 1.0000
4.000 0.6631 0.00897 0.00268 -0.0492 0.0433 1.0000
4.250 0.6898 0.00919 0.00290 -0.0490 0.0394 1.0000
4.500 0.7165 0.00942 0.00315 -0.0488 0.0374 1.0000
4.750 0.7431 0.00965 0.00341 -0.0485 0.0365 1.0000
5.000 0.7695 0.00992 0.00372 -0.0483 0.0349 1.0000
5.250 0.7956 0.01023 0.00406 -0.0480 0.0331 1.0000
5.500 0.8213 0.01059 0.00445 -0.0476 0.0312 1.0000
5.750 0.8465 0.01104 0.00494 -0.0472 0.0293 1.0000
6.000 0.8697 0.01179 0.00581 -0.0464 0.0272 1.0000
6.250 0.8961 0.01199 0.00603 -0.0462 0.0266 1.0000
6.500 0.9227 0.01216 0.00621 -0.0461 0.0258 1.0000
6.750 0.9491 0.01235 0.00641 -0.0459 0.0243 1.0000
7.000 0.9752 0.01258 0.00666 -0.0457 0.0222 1.0000
7.250 1.0008 0.01286 0.00693 -0.0454 0.0201 1.0000
7.500 1.0235 0.01358 0.00772 -0.0447 0.0176 1.0000
7.750 1.0508 0.01360 0.00773 -0.0446 0.0162 1.0000
8.000 1.0773 0.01372 0.00781 -0.0445 0.0143 1.0000
8.250 1.0995 0.01449 0.00860 -0.0437 0.0118 1.0000
8.500 1.1243 0.01484 0.00898 -0.0433 0.0111 1.0000
8.750 1.1483 0.01527 0.00947 -0.0428 0.0102 1.0000
9.000 1.1718 0.01576 0.00997 -0.0422 0.0094 1.0000
9.250 1.1912 0.01681 0.01111 -0.0410 0.0083 1.0000
9.500 1.2107 0.01780 0.01222 -0.0398 0.0079 1.0000
9.750 1.2331 0.01836 0.01286 -0.0391 0.0075 1.0000
10.000 1.2545 0.01902 0.01359 -0.0383 0.0071 1.0000
10.250 1.2753 0.01972 0.01436 -0.0374 0.0067 1.0000
10.500 1.2952 0.02050 0.01520 -0.0364 0.0064 1.0000
10.750 1.3133 0.02144 0.01625 -0.0353 0.0060 1.0000
11.000 1.3251 0.02309 0.01807 -0.0332 0.0057 1.0000
11.250 1.3301 0.02552 0.02077 -0.0304 0.0054 1.0000
11.500 1.3452 0.02657 0.02194 -0.0289 0.0053 1.0000
11.750 1.3576 0.02781 0.02332 -0.0272 0.0052 1.0000
12.000 1.3658 0.02918 0.02485 -0.0248 0.0051 1.0000
12.250 1.3699 0.03070 0.02651 -0.0221 0.0050 1.0000
12.500 1.3719 0.03238 0.02836 -0.0194 0.0049 1.0000
12.750 1.3714 0.03437 0.03051 -0.0170 0.0048 1.0000
13.000 1.3699 0.03655 0.03285 -0.0150 0.0047 1.0000
13.250 1.3655 0.03921 0.03568 -0.0135 0.0047 1.0000
13.500 1.3592 0.04231 0.03896 -0.0126 0.0046 1.0000
13.750 1.3513 0.04592 0.04275 -0.0126 0.0046 1.0000
14.000 1.3399 0.05038 0.04740 -0.0134 0.0045 1.0000
14.250 1.3277 0.05541 0.05261 -0.0152 0.0045 1.0000
14.500 1.3111 0.06165 0.05903 -0.0182 0.0045 1.0000
14.750 1.2908 0.06902 0.06658 -0.0222 0.0045 1.0000
15.000 1.2658 0.07780 0.07554 -0.0273 0.0045 1.0000
15.250 1.2337 0.08851 0.08643 -0.0335 0.0046 1.0000
15.500 1.1937 0.10179 0.09991 -0.0411 0.0047 1.0000
15.750 1.1480 0.11729 0.11558 -0.0495 0.0049 1.0000
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