NACA 1408 (naca1408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.22 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1408-il-1000000-n5.txt Download as CSV file: xf-naca1408-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1408
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
------ -------- --------- --------- -------- -------- --------
-13.750 -1.1374 0.04733 0.04513 -0.0315 1.0000 0.0032
-13.500 -1.1667 0.03979 0.03732 -0.0373 1.0000 0.0032
-13.250 -1.1762 0.03640 0.03374 -0.0365 1.0000 0.0032
-13.000 -1.1740 0.03364 0.03078 -0.0360 1.0000 0.0032
-12.750 -1.1663 0.03136 0.02831 -0.0354 1.0000 0.0033
-12.500 -1.1550 0.02939 0.02616 -0.0347 1.0000 0.0033
-12.250 -1.1413 0.02763 0.02422 -0.0341 1.0000 0.0034
-12.000 -1.1256 0.02606 0.02247 -0.0334 1.0000 0.0035
-11.750 -1.1084 0.02462 0.02087 -0.0328 1.0000 0.0036
-11.500 -1.0901 0.02330 0.01939 -0.0322 1.0000 0.0037
-11.250 -1.0706 0.02211 0.01804 -0.0316 1.0000 0.0038
-11.000 -1.0502 0.02101 0.01679 -0.0310 1.0000 0.0039
-10.750 -1.0291 0.02000 0.01564 -0.0304 1.0000 0.0040
-10.500 -1.0072 0.01909 0.01461 -0.0299 1.0000 0.0042
-10.250 -0.9848 0.01827 0.01366 -0.0294 1.0000 0.0042
-10.000 -0.9629 0.01730 0.01254 -0.0288 1.0000 0.0044
-9.750 -0.9405 0.01640 0.01153 -0.0282 1.0000 0.0047
-9.500 -0.9171 0.01574 0.01079 -0.0278 1.0000 0.0050
-9.250 -0.8932 0.01517 0.01016 -0.0273 1.0000 0.0052
-9.000 -0.8693 0.01461 0.00953 -0.0268 1.0000 0.0055
-8.750 -0.8453 0.01406 0.00890 -0.0263 1.0000 0.0058
-8.500 -0.8214 0.01355 0.00831 -0.0257 1.0000 0.0060
-8.250 -0.7973 0.01308 0.00777 -0.0251 1.0000 0.0063
-8.000 -0.7739 0.01251 0.00711 -0.0244 1.0000 0.0067
-7.750 -0.7503 0.01203 0.00658 -0.0237 1.0000 0.0073
-7.500 -0.7265 0.01162 0.00613 -0.0230 1.0000 0.0078
-7.250 -0.7025 0.01126 0.00573 -0.0223 1.0000 0.0084
-7.000 -0.6785 0.01093 0.00536 -0.0216 1.0000 0.0090
-6.750 -0.6548 0.01055 0.00495 -0.0208 1.0000 0.0103
-6.500 -0.6253 0.01020 0.00459 -0.0213 0.9988 0.0118
-6.250 -0.5934 0.00989 0.00424 -0.0224 0.9971 0.0132
-6.000 -0.5609 0.00958 0.00396 -0.0235 0.9953 0.0168
-5.750 -0.5288 0.00935 0.00373 -0.0246 0.9931 0.0196
-5.500 -0.4967 0.00909 0.00347 -0.0256 0.9901 0.0225
-5.250 -0.4641 0.00887 0.00325 -0.0267 0.9873 0.0254
-5.000 -0.4326 0.00869 0.00307 -0.0276 0.9834 0.0276
-4.750 -0.4015 0.00855 0.00290 -0.0283 0.9785 0.0288
-4.500 -0.3703 0.00841 0.00275 -0.0291 0.9736 0.0294
-4.250 -0.3406 0.00815 0.00245 -0.0294 0.9666 0.0318
-4.000 -0.3112 0.00794 0.00224 -0.0297 0.9587 0.0345
-3.750 -0.2824 0.00777 0.00205 -0.0299 0.9496 0.0360
-3.250 -0.2274 0.00751 0.00172 -0.0295 0.9259 0.0387
-3.000 -0.2003 0.00739 0.00157 -0.0292 0.9120 0.0426
-2.750 -0.1735 0.00726 0.00144 -0.0289 0.8967 0.0512
-2.500 -0.1470 0.00706 0.00129 -0.0286 0.8802 0.0780
-2.250 -0.1204 0.00690 0.00117 -0.0283 0.8628 0.1034
-2.000 -0.0935 0.00676 0.00107 -0.0280 0.8437 0.1296
-1.750 -0.0668 0.00664 0.00098 -0.0277 0.8230 0.1615
-1.500 -0.0399 0.00652 0.00090 -0.0275 0.8011 0.1948
-1.250 -0.0132 0.00639 0.00083 -0.0273 0.7771 0.2393
-1.000 0.0137 0.00631 0.00078 -0.0271 0.7505 0.2774
-0.750 0.0405 0.00621 0.00074 -0.0269 0.7229 0.3236
-0.500 0.0675 0.00614 0.00071 -0.0268 0.6959 0.3659
-0.250 0.0945 0.00607 0.00069 -0.0266 0.6696 0.4125
0.000 0.1208 0.00585 0.00068 -0.0265 0.6433 0.5036
0.250 0.1463 0.00561 0.00070 -0.0261 0.6083 0.6178
0.500 0.1715 0.00557 0.00073 -0.0256 0.5564 0.6995
0.750 0.1971 0.00563 0.00077 -0.0252 0.5052 0.7524
1.000 0.2230 0.00562 0.00082 -0.0247 0.4743 0.8042
1.250 0.2478 0.00569 0.00090 -0.0240 0.4299 0.8536
1.500 0.2719 0.00584 0.00099 -0.0231 0.3760 0.8974
1.750 0.2970 0.00598 0.00107 -0.0224 0.3407 0.9352
2.000 0.3256 0.00623 0.00118 -0.0225 0.2923 0.9606
2.250 0.3571 0.00653 0.00130 -0.0235 0.2438 0.9764
2.500 0.3903 0.00688 0.00144 -0.0248 0.1902 0.9879
2.750 0.4249 0.00724 0.00160 -0.0265 0.1429 0.9965
3.000 0.4562 0.00756 0.00176 -0.0275 0.1051 1.0000
3.250 0.4813 0.00783 0.00192 -0.0270 0.0794 1.0000
3.500 0.5065 0.00813 0.00210 -0.0265 0.0536 1.0000
3.750 0.5322 0.00837 0.00227 -0.0261 0.0412 1.0000
4.000 0.5583 0.00859 0.00246 -0.0257 0.0349 1.0000
4.250 0.5847 0.00876 0.00264 -0.0254 0.0336 1.0000
4.500 0.6111 0.00895 0.00284 -0.0251 0.0326 1.0000
4.750 0.6376 0.00915 0.00305 -0.0249 0.0313 1.0000
5.000 0.6639 0.00937 0.00328 -0.0246 0.0295 1.0000
5.250 0.6902 0.00962 0.00352 -0.0243 0.0277 1.0000
5.500 0.7163 0.00991 0.00384 -0.0240 0.0259 1.0000
5.750 0.7426 0.01015 0.00410 -0.0238 0.0249 1.0000
6.000 0.7694 0.01031 0.00429 -0.0236 0.0243 1.0000
6.250 0.7959 0.01050 0.00451 -0.0234 0.0230 1.0000
6.500 0.8223 0.01072 0.00474 -0.0232 0.0205 1.0000
6.750 0.8482 0.01102 0.00500 -0.0230 0.0166 1.0000
7.000 0.8741 0.01132 0.00529 -0.0227 0.0141 1.0000
7.250 0.8996 0.01168 0.00563 -0.0224 0.0114 1.0000
7.500 0.9252 0.01204 0.00603 -0.0220 0.0102 1.0000
7.750 0.9504 0.01243 0.00645 -0.0217 0.0091 1.0000
8.000 0.9752 0.01289 0.00693 -0.0213 0.0079 1.0000
8.250 1.0000 0.01334 0.00742 -0.0209 0.0072 1.0000
8.500 1.0248 0.01376 0.00789 -0.0205 0.0067 1.0000
8.750 1.0493 0.01423 0.00841 -0.0201 0.0062 1.0000
9.000 1.0734 0.01474 0.00897 -0.0196 0.0058 1.0000
9.250 1.0968 0.01535 0.00965 -0.0190 0.0053 1.0000
9.500 1.1196 0.01604 0.01042 -0.0184 0.0050 1.0000
9.750 1.1430 0.01660 0.01106 -0.0179 0.0048 1.0000
10.000 1.1659 0.01721 0.01175 -0.0173 0.0046 1.0000
10.250 1.1883 0.01788 0.01250 -0.0166 0.0044 1.0000
10.500 1.2103 0.01857 0.01329 -0.0159 0.0043 1.0000
10.750 1.2319 0.01928 0.01407 -0.0152 0.0041 1.0000
11.000 1.2531 0.02001 0.01488 -0.0145 0.0039 1.0000
11.250 1.2735 0.02081 0.01578 -0.0137 0.0037 1.0000
11.500 1.2924 0.02178 0.01684 -0.0128 0.0035 1.0000
11.750 1.3080 0.02311 0.01832 -0.0115 0.0033 1.0000
12.000 1.3260 0.02405 0.01937 -0.0105 0.0032 1.0000
12.250 1.3426 0.02509 0.02054 -0.0093 0.0032 1.0000
12.500 1.3577 0.02622 0.02181 -0.0080 0.0031 1.0000
12.750 1.3710 0.02745 0.02318 -0.0066 0.0030 1.0000
13.000 1.3823 0.02878 0.02464 -0.0050 0.0030 1.0000
13.250 1.3900 0.03019 0.02619 -0.0030 0.0029 1.0000
13.500 1.3927 0.03173 0.02789 -0.0005 0.0029 1.0000
13.750 1.3935 0.03349 0.02980 0.0017 0.0028 1.0000
14.000 1.3915 0.03563 0.03209 0.0035 0.0028 1.0000
14.250 1.3880 0.03817 0.03478 0.0045 0.0027 1.0000
14.500 1.3819 0.04133 0.03810 0.0046 0.0027 1.0000
14.750 1.3729 0.04534 0.04227 0.0036 0.0027 1.0000
15.000 1.3606 0.05045 0.04756 0.0011 0.0027 1.0000
15.250 1.3422 0.05736 0.05466 -0.0032 0.0027 1.0000
15.500 1.3165 0.06643 0.06393 -0.0094 0.0027 1.0000
15.750 1.2739 0.07967 0.07740 -0.0180 0.0027 1.0000
16.000 1.2028 0.09943 0.09738 -0.0290 0.0028 1.0000
16.250 1.1078 0.12434 0.12248 -0.0414 0.0031 1.0000
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