USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: USA 27 AIRFOIL (usa27-il) Reynolds number: 100,000 Max Cl/Cd: 50.46 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa27-il-100000.txt Download as CSV file: xf-usa27-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3966 0.09458 0.09054 -0.0161 1.0000 0.0968
-6.500 -0.4091 0.09274 0.08874 -0.0171 1.0000 0.0997
-6.250 -0.4262 0.09175 0.08766 -0.0245 1.0000 0.1019
-6.000 -0.4228 0.08724 0.08330 -0.0189 1.0000 0.1033
-5.750 -0.4209 0.08490 0.08102 -0.0153 1.0000 0.1056
-5.500 -0.3875 0.08087 0.07675 -0.0286 0.9917 0.1168
-5.250 -0.3648 0.07686 0.07285 -0.0269 0.9863 0.1210
-5.000 -0.3260 0.07242 0.06819 -0.0370 0.9754 0.1327
-4.750 -0.2893 0.06938 0.06503 -0.0420 0.9653 0.1445
-4.500 -0.2548 0.06477 0.06040 -0.0460 0.9582 0.1512
-4.250 -0.2213 0.06133 0.05679 -0.0511 0.9464 0.1646
-4.000 -0.1893 0.05835 0.05369 -0.0546 0.9356 0.1799
-3.750 -0.1483 0.05502 0.05025 -0.0591 0.9294 0.1966
-3.500 -0.1201 0.05241 0.04751 -0.0611 0.9176 0.2122
-3.250 -0.0900 0.04978 0.04479 -0.0630 0.9073 0.2288
-3.000 -0.0505 0.04681 0.04174 -0.0662 0.9008 0.2480
-2.750 -0.0202 0.04521 0.03990 -0.0679 0.8890 0.2744
-2.500 0.0514 0.03457 0.02759 -0.0766 0.8859 0.1243
-2.250 0.0883 0.03098 0.02284 -0.0766 0.8763 0.1011
-2.000 0.1346 0.02841 0.02001 -0.0794 0.8711 0.0966
-1.750 0.1695 0.02684 0.01809 -0.0799 0.8610 0.0932
-1.500 0.2182 0.02517 0.01611 -0.0827 0.8559 0.0913
-1.250 0.2535 0.02408 0.01494 -0.0834 0.8457 0.0928
-1.000 0.3001 0.02275 0.01357 -0.0860 0.8401 0.0963
-0.750 0.3323 0.02188 0.01267 -0.0860 0.8285 0.0979
-0.500 0.3787 0.02066 0.01140 -0.0883 0.8228 0.1012
-0.250 0.4085 0.01995 0.01073 -0.0879 0.8096 0.1066
0.000 0.4412 0.01932 0.01012 -0.0880 0.7967 0.1190
0.250 0.4749 0.01836 0.00976 -0.0884 0.7839 0.2666
0.500 0.6026 0.01597 0.00890 -0.1072 0.7726 1.0000
0.750 0.6299 0.01586 0.00857 -0.1065 0.7545 1.0000
1.000 0.6576 0.01579 0.00826 -0.1059 0.7360 1.0000
1.250 0.6859 0.01574 0.00798 -0.1054 0.7175 1.0000
1.500 0.7144 0.01575 0.00774 -0.1050 0.6991 1.0000
1.750 0.7380 0.01593 0.00773 -0.1039 0.6791 1.0000
2.000 0.7631 0.01617 0.00776 -0.1031 0.6606 1.0000
2.250 0.7881 0.01647 0.00787 -0.1023 0.6435 1.0000
2.500 0.8123 0.01684 0.00807 -0.1015 0.6275 1.0000
2.750 0.8358 0.01724 0.00833 -0.1005 0.6124 1.0000
3.000 0.8589 0.01765 0.00860 -0.0995 0.5983 1.0000
3.250 0.8825 0.01805 0.00888 -0.0986 0.5855 1.0000
3.500 0.9062 0.01843 0.00915 -0.0978 0.5737 1.0000
3.750 0.9257 0.01883 0.00953 -0.0962 0.5613 1.0000
4.000 0.9467 0.01920 0.00985 -0.0948 0.5497 1.0000
4.250 0.9704 0.01953 0.01007 -0.0939 0.5395 1.0000
4.500 0.9904 0.01989 0.01043 -0.0925 0.5289 1.0000
4.750 1.0111 0.02027 0.01081 -0.0911 0.5191 1.0000
5.000 1.0361 0.02056 0.01099 -0.0905 0.5102 1.0000
5.250 1.0536 0.02098 0.01150 -0.0886 0.5003 1.0000
5.500 1.0778 0.02136 0.01182 -0.0880 0.4927 1.0000
5.750 1.0972 0.02181 0.01234 -0.0864 0.4840 1.0000
6.000 1.1204 0.02223 0.01276 -0.0856 0.4763 1.0000
6.250 1.1404 0.02267 0.01324 -0.0842 0.4676 1.0000
6.500 1.1622 0.02314 0.01373 -0.0832 0.4595 1.0000
6.750 1.1838 0.02357 0.01421 -0.0821 0.4510 1.0000
7.000 1.2037 0.02412 0.01484 -0.0808 0.4428 1.0000
7.250 1.2271 0.02457 0.01529 -0.0800 0.4344 1.0000
7.500 1.2444 0.02518 0.01603 -0.0783 0.4255 1.0000
7.750 1.2709 0.02561 0.01639 -0.0780 0.4164 1.0000
8.000 1.2848 0.02602 0.01693 -0.0756 0.4044 1.0000
8.250 1.3000 0.02631 0.01727 -0.0733 0.3910 1.0000
8.500 1.3148 0.02652 0.01749 -0.0709 0.3770 1.0000
8.750 1.3298 0.02678 0.01776 -0.0686 0.3638 1.0000
9.000 1.3472 0.02709 0.01808 -0.0668 0.3520 1.0000
9.250 1.3614 0.02735 0.01836 -0.0645 0.3395 1.0000
9.500 1.3687 0.02766 0.01881 -0.0610 0.3265 1.0000
9.750 1.3777 0.02808 0.01934 -0.0580 0.3147 1.0000
10.000 1.3874 0.02847 0.01982 -0.0551 0.3036 1.0000
10.250 1.3944 0.02877 0.02014 -0.0517 0.2922 1.0000
10.500 1.3930 0.02919 0.02068 -0.0471 0.2797 1.0000
10.750 1.3943 0.02979 0.02141 -0.0432 0.2675 1.0000
11.000 1.3979 0.03049 0.02223 -0.0399 0.2562 1.0000
11.250 1.3996 0.03132 0.02314 -0.0366 0.2434 1.0000
11.500 1.4015 0.03233 0.02424 -0.0336 0.2308 1.0000
11.750 1.4027 0.03354 0.02552 -0.0309 0.2179 1.0000
12.000 1.4007 0.03510 0.02710 -0.0282 0.2022 1.0000
12.250 1.3975 0.03697 0.02898 -0.0257 0.1878 1.0000
12.500 1.3930 0.03916 0.03117 -0.0235 0.1746 1.0000
12.750 1.3856 0.04181 0.03383 -0.0216 0.1602 1.0000
13.000 1.3785 0.04469 0.03678 -0.0201 0.1454 1.0000
13.500 1.3551 0.05217 0.04430 -0.0184 0.0968 1.0000
13.750 1.3348 0.05733 0.04937 -0.0184 0.0803 1.0000
14.000 1.3152 0.06273 0.05476 -0.0189 0.0694 1.0000
14.250 1.2967 0.06827 0.06034 -0.0196 0.0627 1.0000
14.500 1.2792 0.07391 0.06606 -0.0206 0.0586 1.0000
14.750 1.2620 0.07971 0.07194 -0.0219 0.0559 1.0000
15.000 1.2467 0.08541 0.07775 -0.0233 0.0540 1.0000
15.250 1.2325 0.09106 0.08354 -0.0247 0.0524 1.0000
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