USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 27 mod. AIRFOIL (usa27m2-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.03 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa27m2-il-1000000.txt Download as CSV file: xf-usa27m2-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 mod. 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1803 0.05994 0.05816 -0.1110 0.9707 0.0247
-8.750 -0.1774 0.05695 0.05515 -0.1124 0.9611 0.0248
-8.500 -0.1694 0.05356 0.05171 -0.1148 0.9535 0.0250
-8.250 -0.1606 0.04998 0.04806 -0.1170 0.9452 0.0252
-8.000 -0.1542 0.04588 0.04387 -0.1185 0.9345 0.0254
-7.750 -0.1561 0.03735 0.03505 -0.1215 0.9231 0.0260
-7.500 -0.1499 0.03318 0.03058 -0.1213 0.9137 0.0266
-7.250 -0.1449 0.02951 0.02650 -0.1194 0.9033 0.0281
-7.000 -0.1317 0.02861 0.02507 -0.1172 0.8947 0.0288
-6.750 -0.1321 0.02365 0.01962 -0.1142 0.8849 0.0293
-6.500 -0.1116 0.02203 0.01798 -0.1134 0.8766 0.0297
-6.250 -0.0901 0.02093 0.01680 -0.1126 0.8680 0.0300
-6.000 -0.0687 0.02002 0.01582 -0.1117 0.8598 0.0305
-5.750 -0.0468 0.01917 0.01484 -0.1108 0.8518 0.0311
-5.500 -0.0252 0.01833 0.01384 -0.1096 0.8439 0.0321
-5.250 0.0008 0.01926 0.01452 -0.1086 0.8352 0.0338
-5.000 0.0159 0.01633 0.01134 -0.1067 0.8264 0.0351
-4.750 0.0397 0.01555 0.01051 -0.1060 0.8165 0.0357
-4.500 0.0631 0.01493 0.00983 -0.1052 0.8052 0.0364
-4.250 0.0868 0.01444 0.00923 -0.1042 0.7931 0.0375
-4.000 0.1107 0.01424 0.00888 -0.1031 0.7794 0.0389
-3.750 0.1348 0.01237 0.00653 -0.1012 0.7637 0.0293
-3.500 0.1578 0.01185 0.00591 -0.1001 0.7418 0.0293
-3.250 0.1791 0.01156 0.00547 -0.0985 0.7118 0.0292
-3.000 0.1992 0.01134 0.00509 -0.0968 0.6797 0.0292
-2.250 0.2645 0.01040 0.00389 -0.0927 0.6250 0.0296
-2.000 0.2876 0.01016 0.00361 -0.0916 0.6133 0.0299
-1.750 0.3106 0.01000 0.00339 -0.0906 0.6023 0.0302
-1.500 0.3348 0.00982 0.00320 -0.0897 0.5918 0.0304
-1.250 0.3585 0.00970 0.00302 -0.0888 0.5811 0.0307
-1.000 0.3818 0.00961 0.00288 -0.0877 0.5678 0.0310
-0.750 0.4051 0.00953 0.00274 -0.0867 0.5523 0.0313
-0.500 0.4283 0.00949 0.00263 -0.0857 0.5339 0.0319
-0.250 0.4511 0.00948 0.00254 -0.0845 0.5120 0.0326
0.000 0.4725 0.00955 0.00248 -0.0832 0.4858 0.0332
0.250 0.4942 0.00963 0.00244 -0.0819 0.4606 0.0337
0.500 0.5161 0.00971 0.00241 -0.0806 0.4398 0.0343
0.750 0.5386 0.00976 0.00237 -0.0795 0.4238 0.0355
1.000 0.5621 0.00981 0.00236 -0.0785 0.4120 0.0370
1.250 0.5856 0.00988 0.00237 -0.0776 0.4021 0.0387
1.500 0.6102 0.00990 0.00238 -0.0769 0.3943 0.0431
1.750 0.6298 0.00961 0.00245 -0.0754 0.3867 0.1937
2.000 0.6532 0.00952 0.00255 -0.0746 0.3809 0.2679
2.250 0.6771 0.00954 0.00265 -0.0738 0.3746 0.3070
2.500 0.7008 0.00960 0.00274 -0.0731 0.3686 0.3383
2.750 0.7254 0.00958 0.00282 -0.0725 0.3641 0.3761
3.000 0.7393 0.00886 0.00289 -0.0699 0.3597 0.7019
3.250 0.7732 0.00861 0.00334 -0.0710 0.3535 0.9646
3.500 0.8152 0.00886 0.00357 -0.0741 0.3482 0.9798
3.750 0.8736 0.00921 0.00384 -0.0810 0.3415 0.9863
4.000 0.9212 0.00949 0.00406 -0.0856 0.3360 0.9908
4.250 0.9595 0.00965 0.00421 -0.0880 0.3327 0.9937
4.500 1.0048 0.00981 0.00434 -0.0921 0.3283 0.9955
4.750 1.0459 0.01000 0.00448 -0.0953 0.3232 0.9975
5.000 1.0853 0.01016 0.00461 -0.0981 0.3189 0.9993
5.250 1.1141 0.01025 0.00472 -0.0985 0.3157 1.0000
5.500 1.1323 0.01037 0.00483 -0.0966 0.3120 1.0000
5.750 1.1486 0.01053 0.00496 -0.0944 0.3064 1.0000
6.000 1.1657 0.01065 0.00508 -0.0923 0.3023 1.0000
6.250 1.1828 0.01075 0.00518 -0.0901 0.2986 1.0000
6.500 1.1953 0.01087 0.00530 -0.0871 0.2938 1.0000
6.750 1.2045 0.01103 0.00543 -0.0833 0.2882 1.0000
7.000 1.2186 0.01111 0.00553 -0.0806 0.2840 1.0000
7.250 1.2321 0.01125 0.00566 -0.0777 0.2786 1.0000
7.500 1.2446 0.01144 0.00583 -0.0748 0.2723 1.0000
7.750 1.2601 0.01159 0.00598 -0.0724 0.2648 1.0000
8.000 1.2737 0.01184 0.00618 -0.0698 0.2543 1.0000
8.250 1.2866 0.01215 0.00642 -0.0671 0.2397 1.0000
8.500 1.2967 0.01262 0.00676 -0.0640 0.2162 1.0000
8.750 1.3031 0.01330 0.00726 -0.0603 0.1895 1.0000
9.000 1.3144 0.01382 0.00770 -0.0576 0.1766 1.0000
9.250 1.3280 0.01429 0.00814 -0.0553 0.1675 1.0000
9.500 1.3411 0.01482 0.00861 -0.0531 0.1589 1.0000
9.750 1.3570 0.01525 0.00904 -0.0513 0.1515 1.0000
10.000 1.3703 0.01583 0.00957 -0.0492 0.1418 1.0000
10.250 1.3817 0.01654 0.01018 -0.0470 0.1244 1.0000
10.500 1.3734 0.01834 0.01163 -0.0420 0.0783 1.0000
10.750 1.3524 0.02097 0.01398 -0.0357 0.0252 1.0000
11.000 1.3599 0.02206 0.01508 -0.0334 0.0193 1.0000
11.250 1.3700 0.02304 0.01610 -0.0315 0.0175 1.0000
11.500 1.3814 0.02395 0.01706 -0.0299 0.0167 1.0000
11.750 1.3918 0.02495 0.01811 -0.0283 0.0159 1.0000
12.000 1.4007 0.02609 0.01930 -0.0266 0.0153 1.0000
12.250 1.4078 0.02740 0.02068 -0.0249 0.0147 1.0000
12.500 1.4123 0.02897 0.02232 -0.0231 0.0141 1.0000
12.750 1.4209 0.03026 0.02367 -0.0217 0.0138 1.0000
13.000 1.4281 0.03172 0.02519 -0.0204 0.0135 1.0000
13.250 1.4340 0.03335 0.02689 -0.0192 0.0132 1.0000
13.500 1.4388 0.03516 0.02877 -0.0180 0.0129 1.0000
13.750 1.4423 0.03714 0.03083 -0.0170 0.0126 1.0000
14.000 1.4444 0.03936 0.03312 -0.0161 0.0123 1.0000
14.250 1.4447 0.04188 0.03573 -0.0153 0.0121 1.0000
14.500 1.4415 0.04491 0.03884 -0.0147 0.0118 1.0000
14.750 1.4331 0.04862 0.04267 -0.0143 0.0115 1.0000
15.000 1.4235 0.05263 0.04680 -0.0141 0.0113 1.0000
15.250 1.4225 0.05570 0.04996 -0.0141 0.0112 1.0000
15.500 1.4185 0.05919 0.05355 -0.0142 0.0111 1.0000
15.750 1.4125 0.06298 0.05743 -0.0145 0.0110 1.0000
16.000 1.4052 0.06704 0.06159 -0.0149 0.0109 1.0000
16.250 1.3964 0.07141 0.06606 -0.0155 0.0108 1.0000
16.500 1.3863 0.07602 0.07077 -0.0163 0.0107 1.0000
16.750 1.3756 0.08077 0.07563 -0.0171 0.0106 1.0000
17.000 1.3639 0.08575 0.08072 -0.0182 0.0105 1.0000
17.250 1.3522 0.09080 0.08587 -0.0193 0.0104 1.0000
17.500 1.3402 0.09590 0.09106 -0.0205 0.0103 1.0000
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Polar data table (+)
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