USA 26 AIRFOIL (usa26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: USA 26 AIRFOIL (usa26-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.56 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa26-il-1000000.txt Download as CSV file: xf-usa26-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: USA 26 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3807 0.12073 0.11907 -0.0252 1.0000 0.0151
-11.000 -0.3807 0.11747 0.11583 -0.0254 1.0000 0.0151
-10.750 -0.3810 0.11404 0.11241 -0.0247 1.0000 0.0155
-10.500 -0.3778 0.11197 0.11036 -0.0242 1.0000 0.0156
-10.250 -0.3736 0.11036 0.10876 -0.0236 1.0000 0.0159
-10.000 -0.3719 0.10819 0.10661 -0.0232 1.0000 0.0162
-9.750 -0.3707 0.10569 0.10412 -0.0231 0.9999 0.0168
-9.250 -0.3547 0.09422 0.09265 -0.0350 0.9971 0.0189
-9.000 -0.3455 0.08920 0.08763 -0.0396 0.9956 0.0189
-8.500 -0.3408 0.07597 0.07441 -0.0528 0.9895 0.0193
-8.250 -0.3172 0.07457 0.07299 -0.0557 0.9872 0.0197
-8.000 -0.2925 0.07321 0.07163 -0.0587 0.9854 0.0204
-7.750 -0.2712 0.06872 0.06712 -0.0660 0.9834 0.0216
-7.000 -0.2380 0.01399 0.01140 -0.0933 0.9609 0.0239
-6.750 -0.2565 0.02276 0.01947 -0.0921 0.9596 0.0241
-6.500 -0.1855 0.03986 0.03778 -0.0930 0.9619 0.0256
-6.250 -0.1600 0.03372 0.03140 -0.0969 0.9590 0.0270
-6.000 -0.1556 0.02575 0.02285 -0.0959 0.9510 0.0271
-5.750 -0.1413 0.02120 0.01779 -0.0945 0.9443 0.0270
-5.500 -0.1249 0.01842 0.01462 -0.0926 0.9369 0.0274
-5.250 -0.1027 0.01653 0.01244 -0.0917 0.9299 0.0279
-5.000 -0.0788 0.01557 0.01129 -0.0908 0.9220 0.0285
-4.750 -0.0476 0.01616 0.01181 -0.0911 0.9143 0.0295
-4.500 -0.0248 0.01493 0.01040 -0.0901 0.9038 0.0295
-4.250 -0.0013 0.01324 0.00845 -0.0893 0.8925 0.0296
-4.000 0.0229 0.01153 0.00650 -0.0886 0.8790 0.0299
-3.750 0.0483 0.01060 0.00545 -0.0880 0.8622 0.0308
-3.500 0.0739 0.01028 0.00503 -0.0875 0.8430 0.0315
-3.250 0.0984 0.00992 0.00455 -0.0866 0.8219 0.0319
-3.000 0.1222 0.00969 0.00421 -0.0855 0.7995 0.0324
-2.750 0.1452 0.00945 0.00385 -0.0843 0.7763 0.0329
-2.500 0.1674 0.00924 0.00351 -0.0830 0.7494 0.0333
-2.250 0.1886 0.00909 0.00321 -0.0814 0.7167 0.0337
-2.000 0.2084 0.00902 0.00295 -0.0795 0.6735 0.0342
-1.750 0.2270 0.00905 0.00275 -0.0774 0.6191 0.0347
-1.500 0.2466 0.00911 0.00260 -0.0756 0.5720 0.0354
-1.250 0.2692 0.00916 0.00252 -0.0743 0.5441 0.0361
-1.000 0.2928 0.00918 0.00244 -0.0734 0.5238 0.0367
-0.750 0.3155 0.00895 0.00211 -0.0722 0.5087 0.0379
-0.500 0.3393 0.00883 0.00194 -0.0712 0.4958 0.0396
-0.250 0.3638 0.00881 0.00186 -0.0704 0.4840 0.0412
0.250 0.4134 0.00878 0.00175 -0.0690 0.4612 0.0452
0.500 0.4379 0.00874 0.00166 -0.0682 0.4504 0.0497
0.750 0.4623 0.00874 0.00164 -0.0674 0.4395 0.0576
1.000 0.4837 0.00845 0.00160 -0.0661 0.4290 0.1678
1.250 0.5067 0.00834 0.00166 -0.0651 0.4189 0.2435
1.500 0.5307 0.00835 0.00172 -0.0643 0.4086 0.2826
1.750 0.5551 0.00839 0.00177 -0.0635 0.3977 0.3109
2.000 0.5793 0.00841 0.00183 -0.0627 0.3872 0.3415
2.250 0.6023 0.00838 0.00190 -0.0618 0.3773 0.3951
2.500 0.6242 0.00717 0.00214 -0.0606 0.3690 0.9512
2.750 0.6931 0.00755 0.00245 -0.0697 0.3588 0.9787
3.000 0.7453 0.00784 0.00266 -0.0752 0.3505 0.9861
3.250 0.7860 0.00798 0.00277 -0.0781 0.3449 0.9892
3.500 0.8229 0.00814 0.00289 -0.0801 0.3394 0.9924
3.750 0.8653 0.00832 0.00302 -0.0835 0.3335 0.9952
4.000 0.9133 0.00840 0.00309 -0.0881 0.3290 0.9982
4.250 0.9516 0.00853 0.00317 -0.0905 0.3218 1.0000
4.500 0.9738 0.00863 0.00327 -0.0894 0.3170 1.0000
4.750 0.9959 0.00873 0.00336 -0.0882 0.3108 1.0000
5.000 1.0169 0.00889 0.00348 -0.0868 0.3044 1.0000
5.250 1.0394 0.00896 0.00357 -0.0858 0.2995 1.0000
5.500 1.0608 0.00909 0.00368 -0.0845 0.2934 1.0000
5.750 1.0820 0.00922 0.00380 -0.0832 0.2844 1.0000
6.000 1.1022 0.00939 0.00393 -0.0817 0.2741 1.0000
6.250 1.1227 0.00955 0.00406 -0.0802 0.2621 1.0000
6.500 1.1415 0.00980 0.00423 -0.0785 0.2427 1.0000
6.750 1.1521 0.01051 0.00460 -0.0753 0.1851 1.0000
7.000 1.1627 0.01122 0.00508 -0.0721 0.1493 1.0000
7.250 1.1759 0.01175 0.00548 -0.0694 0.1244 1.0000
7.500 1.1862 0.01244 0.00595 -0.0662 0.0888 1.0000
7.750 1.1817 0.01391 0.00701 -0.0602 0.0204 1.0000
8.000 1.1959 0.01433 0.00743 -0.0576 0.0164 1.0000
8.250 1.2113 0.01468 0.00782 -0.0553 0.0153 1.0000
8.500 1.2255 0.01506 0.00825 -0.0527 0.0145 1.0000
8.750 1.2358 0.01550 0.00873 -0.0494 0.0135 1.0000
9.000 1.2441 0.01604 0.00934 -0.0457 0.0126 1.0000
9.250 1.2570 0.01642 0.00977 -0.0430 0.0123 1.0000
9.500 1.2699 0.01686 0.01025 -0.0404 0.0119 1.0000
9.750 1.2821 0.01736 0.01081 -0.0378 0.0114 1.0000
10.000 1.2941 0.01792 0.01141 -0.0352 0.0110 1.0000
10.250 1.3052 0.01854 0.01209 -0.0325 0.0106 1.0000
10.500 1.3152 0.01923 0.01284 -0.0298 0.0103 1.0000
10.750 1.3216 0.02015 0.01382 -0.0267 0.0099 1.0000
11.000 1.3192 0.02158 0.01538 -0.0226 0.0096 1.0000
11.250 1.3257 0.02257 0.01645 -0.0199 0.0093 1.0000
11.500 1.3341 0.02350 0.01744 -0.0176 0.0092 1.0000
11.750 1.3454 0.02430 0.01829 -0.0158 0.0089 1.0000
12.000 1.3521 0.02542 0.01948 -0.0137 0.0087 1.0000
12.250 1.3555 0.02684 0.02098 -0.0114 0.0085 1.0000
12.500 1.3584 0.02839 0.02261 -0.0094 0.0082 1.0000
12.750 1.3616 0.03004 0.02433 -0.0077 0.0080 1.0000
13.000 1.3617 0.03205 0.02644 -0.0060 0.0080 1.0000
13.250 1.3616 0.03425 0.02872 -0.0048 0.0078 1.0000
13.500 1.3630 0.03645 0.03100 -0.0040 0.0077 1.0000
13.750 1.3601 0.03923 0.03386 -0.0034 0.0075 1.0000
14.000 1.3562 0.04235 0.03708 -0.0031 0.0075 1.0000
14.250 1.3504 0.04589 0.04071 -0.0032 0.0074 1.0000
14.500 1.3404 0.05013 0.04505 -0.0037 0.0072 1.0000
14.750 1.3374 0.05366 0.04866 -0.0044 0.0072 1.0000
15.000 1.3251 0.05831 0.05340 -0.0051 0.0071 1.0000
15.250 1.3124 0.06289 0.05807 -0.0056 0.0070 1.0000
15.500 1.3016 0.06700 0.06224 -0.0057 0.0069 1.0000
15.750 1.2988 0.07057 0.06590 -0.0064 0.0069 1.0000
16.000 1.2962 0.07409 0.06951 -0.0071 0.0068 1.0000
16.250 1.2937 0.07770 0.07320 -0.0079 0.0068 1.0000
16.500 1.2916 0.08152 0.07711 -0.0092 0.0067 1.0000
16.750 1.2886 0.08490 0.08056 -0.0096 0.0067 1.0000
17.000 1.2859 0.08869 0.08444 -0.0107 0.0066 1.0000
17.250 1.2830 0.09265 0.08848 -0.0120 0.0065 1.0000
17.500 1.2794 0.09658 0.09250 -0.0131 0.0064 1.0000
17.750 1.2766 0.10045 0.09645 -0.0144 0.0064 1.0000
18.000 1.2742 0.10407 0.10015 -0.0153 0.0063 1.0000
18.250 1.2697 0.10864 0.10481 -0.0173 0.0061 1.0000
18.500 1.2668 0.11217 0.10843 -0.0180 0.0061 1.0000
18.750 1.2631 0.11651 0.11284 -0.0200 0.0060 1.0000
19.000 1.2590 0.12069 0.11710 -0.0215 0.0059 1.0000
19.250 1.2554 0.12487 0.12136 -0.0232 0.0057 1.0000
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