USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 25 AIRFOIL (usa25-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.57 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa25-il-1000000.txt Download as CSV file: xf-usa25-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: USA 25 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3706 0.13249 0.13083 -0.0203 1.0000 0.0135
-11.500 -0.3695 0.12938 0.12773 -0.0208 1.0000 0.0136
-11.250 -0.3689 0.12601 0.12437 -0.0212 1.0000 0.0136
-11.000 -0.3665 0.12271 0.12108 -0.0204 1.0000 0.0139
-10.750 -0.3636 0.12024 0.11862 -0.0202 1.0000 0.0140
-10.500 -0.3601 0.11804 0.11644 -0.0199 1.0000 0.0142
-10.250 -0.3564 0.11603 0.11444 -0.0196 1.0000 0.0146
-10.000 -0.3440 0.11277 0.11118 -0.0223 0.9993 0.0152
-9.750 -0.3316 0.10901 0.10742 -0.0255 0.9984 0.0158
-9.500 -0.3238 0.10381 0.10221 -0.0311 0.9970 0.0171
-9.250 -0.3128 0.09930 0.09770 -0.0355 0.9957 0.0172
-8.750 -0.3002 0.08894 0.08735 -0.0438 0.9924 0.0175
-8.500 -0.2858 0.08595 0.08436 -0.0463 0.9902 0.0177
-8.250 -0.2681 0.08364 0.08205 -0.0486 0.9883 0.0180
-8.000 -0.2510 0.08062 0.07902 -0.0525 0.9862 0.0184
-7.750 -0.2327 0.07728 0.07569 -0.0578 0.9842 0.0192
-7.500 -0.2218 0.07367 0.07207 -0.0619 0.9792 0.0199
-7.250 -0.1998 0.06697 0.06531 -0.0728 0.9742 0.0217
-6.750 -0.1663 0.05405 0.05224 -0.0853 0.9653 0.0223
-6.500 -0.1411 0.05168 0.04983 -0.0881 0.9609 0.0226
-6.250 -0.1097 0.04952 0.04763 -0.0918 0.9580 0.0232
-6.000 -0.0550 0.03091 0.02910 -0.0920 0.9332 0.0252
-5.750 -0.0335 0.02634 0.02436 -0.0952 0.9191 0.0273
-5.500 -0.0172 0.02198 0.01983 -0.0967 0.8992 0.0274
-5.250 -0.0269 0.03004 0.02749 -0.1007 0.9188 0.0285
-5.000 0.0027 0.02919 0.02654 -0.1019 0.8993 0.0290
-4.750 0.0211 0.01355 0.01071 -0.0951 0.8104 0.0298
-4.500 0.0383 0.01218 0.00914 -0.0941 0.7832 0.0312
-4.250 0.0392 0.01336 0.00865 -0.0955 0.8152 0.0284
-4.000 0.0606 0.01285 0.00787 -0.0939 0.7852 0.0282
-3.750 0.0804 0.01230 0.00704 -0.0920 0.7479 0.0281
-3.500 0.0965 0.01172 0.00610 -0.0894 0.6817 0.0285
-3.250 0.1108 0.01155 0.00547 -0.0865 0.5884 0.0289
-3.000 0.1301 0.01138 0.00498 -0.0847 0.5244 0.0290
-2.750 0.1527 0.01112 0.00451 -0.0835 0.4925 0.0293
-2.500 0.1766 0.01086 0.00412 -0.0826 0.4743 0.0296
-2.250 0.2013 0.01060 0.00377 -0.0819 0.4630 0.0299
-2.000 0.2261 0.01037 0.00346 -0.0811 0.4548 0.0301
-1.750 0.2512 0.01015 0.00318 -0.0804 0.4483 0.0304
-1.500 0.2759 0.00999 0.00295 -0.0796 0.4421 0.0306
-1.250 0.3013 0.00981 0.00274 -0.0790 0.4380 0.0308
-1.000 0.3264 0.00966 0.00256 -0.0783 0.4334 0.0312
-0.750 0.3512 0.00956 0.00241 -0.0776 0.4293 0.0318
-0.500 0.3761 0.00947 0.00228 -0.0768 0.4256 0.0325
-0.250 0.4016 0.00935 0.00216 -0.0762 0.4230 0.0330
0.000 0.4269 0.00928 0.00206 -0.0755 0.4201 0.0337
0.250 0.4521 0.00923 0.00198 -0.0749 0.4166 0.0343
0.500 0.4767 0.00923 0.00193 -0.0741 0.4126 0.0355
0.750 0.5021 0.00921 0.00189 -0.0735 0.4095 0.0372
1.000 0.5278 0.00916 0.00185 -0.0729 0.4069 0.0407
1.250 0.5524 0.00905 0.00186 -0.0722 0.4040 0.0729
1.500 0.5775 0.00905 0.00189 -0.0716 0.4008 0.0891
1.750 0.6023 0.00907 0.00195 -0.0709 0.3974 0.1066
2.000 0.6273 0.00911 0.00203 -0.0703 0.3947 0.1219
2.250 0.6532 0.00910 0.00208 -0.0699 0.3927 0.1379
2.500 0.6790 0.00911 0.00212 -0.0694 0.3900 0.1505
2.750 0.7047 0.00912 0.00218 -0.0689 0.3869 0.1629
3.000 0.7298 0.00916 0.00224 -0.0683 0.3836 0.1764
3.250 0.7544 0.00925 0.00233 -0.0677 0.3794 0.1913
3.500 0.7801 0.00923 0.00241 -0.0672 0.3773 0.2141
3.750 0.8055 0.00923 0.00248 -0.0667 0.3750 0.2406
4.000 0.8304 0.00920 0.00257 -0.0661 0.3724 0.2837
4.250 0.8291 0.00793 0.00270 -0.0600 0.3705 0.8876
4.500 0.8900 0.00809 0.00300 -0.0674 0.3643 0.9721
4.750 0.9412 0.00819 0.00311 -0.0727 0.3567 0.9848
5.000 0.9817 0.00835 0.00322 -0.0756 0.3471 0.9906
5.250 1.0192 0.00848 0.00334 -0.0779 0.3387 0.9946
5.750 1.1049 0.00887 0.00358 -0.0850 0.3031 1.0000
6.000 1.1206 0.00916 0.00373 -0.0826 0.2746 1.0000
6.250 1.1321 0.00970 0.00403 -0.0795 0.2314 1.0000
6.500 1.1426 0.01035 0.00442 -0.0762 0.1894 1.0000
6.750 1.1554 0.01089 0.00479 -0.0734 0.1600 1.0000
7.000 1.1689 0.01143 0.00516 -0.0707 0.1310 1.0000
7.250 1.1685 0.01281 0.00606 -0.0656 0.0531 1.0000
7.500 1.1764 0.01371 0.00674 -0.0619 0.0179 1.0000
7.750 1.1941 0.01403 0.00709 -0.0600 0.0156 1.0000
8.000 1.2115 0.01437 0.00748 -0.0581 0.0147 1.0000
8.250 1.2276 0.01479 0.00795 -0.0559 0.0137 1.0000
8.500 1.2410 0.01526 0.00848 -0.0532 0.0127 1.0000
8.750 1.2522 0.01577 0.00905 -0.0501 0.0122 1.0000
9.000 1.2667 0.01613 0.00944 -0.0477 0.0117 1.0000
9.250 1.2799 0.01658 0.00994 -0.0451 0.0113 1.0000
9.500 1.2926 0.01709 0.01050 -0.0425 0.0109 1.0000
9.750 1.3049 0.01765 0.01111 -0.0400 0.0105 1.0000
10.000 1.3163 0.01827 0.01178 -0.0373 0.0102 1.0000
10.250 1.3256 0.01902 0.01259 -0.0345 0.0098 1.0000
10.500 1.3314 0.01997 0.01362 -0.0312 0.0095 1.0000
10.750 1.3247 0.02164 0.01542 -0.0264 0.0090 1.0000
11.000 1.3313 0.02264 0.01649 -0.0237 0.0090 1.0000
11.250 1.3446 0.02329 0.01719 -0.0220 0.0088 1.0000
11.500 1.3522 0.02431 0.01829 -0.0198 0.0086 1.0000
11.750 1.3585 0.02548 0.01953 -0.0176 0.0084 1.0000
12.000 1.3634 0.02682 0.02094 -0.0155 0.0083 1.0000
12.250 1.3655 0.02846 0.02266 -0.0134 0.0081 1.0000
12.500 1.3718 0.02990 0.02416 -0.0120 0.0077 1.0000
12.750 1.3724 0.03191 0.02626 -0.0104 0.0076 1.0000
13.000 1.3731 0.03406 0.02850 -0.0092 0.0075 1.0000
13.250 1.3713 0.03662 0.03114 -0.0083 0.0073 1.0000
13.500 1.3702 0.03929 0.03389 -0.0077 0.0072 1.0000
13.750 1.3691 0.04216 0.03683 -0.0076 0.0070 1.0000
14.000 1.3632 0.04573 0.04050 -0.0077 0.0070 1.0000
14.250 1.3592 0.04925 0.04412 -0.0080 0.0070 1.0000
14.500 1.3500 0.05346 0.04841 -0.0086 0.0068 1.0000
14.750 1.3464 0.05704 0.05207 -0.0091 0.0068 1.0000
15.000 1.3359 0.06128 0.05638 -0.0094 0.0067 1.0000
15.250 1.3267 0.06504 0.06018 -0.0092 0.0066 1.0000
15.500 1.3223 0.06814 0.06334 -0.0086 0.0065 1.0000
15.750 1.3216 0.07156 0.06686 -0.0095 0.0064 1.0000
16.000 1.3206 0.07498 0.07036 -0.0103 0.0064 1.0000
16.250 1.3194 0.07791 0.07336 -0.0101 0.0064 1.0000
16.500 1.3182 0.08135 0.07688 -0.0110 0.0063 1.0000
16.750 1.3157 0.08494 0.08056 -0.0118 0.0063 1.0000
17.000 1.3127 0.08898 0.08471 -0.0134 0.0061 1.0000
17.250 1.3108 0.09228 0.08808 -0.0138 0.0061 1.0000
17.500 1.3080 0.09599 0.09187 -0.0148 0.0061 1.0000
17.750 1.3054 0.09950 0.09547 -0.0154 0.0060 1.0000
18.000 1.3014 0.10359 0.09965 -0.0168 0.0059 1.0000
18.250 1.2994 0.10680 0.10296 -0.0170 0.0060 1.0000
18.500 1.2941 0.11116 0.10741 -0.0187 0.0059 1.0000
18.750 1.2889 0.11549 0.11185 -0.0203 0.0058 1.0000
19.000 1.2844 0.11959 0.11605 -0.0216 0.0058 1.0000
19.250 1.2779 0.12438 0.12094 -0.0237 0.0057 1.0000
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