USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 27 mod. AIRFOIL (usa27m2-il) Reynolds number: 500,000 Max Cl/Cd: 84.98 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa27m2-il-500000-n5.txt Download as CSV file: xf-usa27m2-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2066 0.09177 0.08926 -0.0760 0.9795 0.0218
-10.000 -0.2009 0.08699 0.08448 -0.0797 0.9766 0.0219
-9.500 -0.2039 0.07333 0.07082 -0.0914 0.9692 0.0224
-9.000 -0.3000 0.03821 0.03487 -0.1164 0.9371 0.0223
-8.750 -0.2932 0.03442 0.03079 -0.1168 0.9315 0.0224
-8.500 -0.2864 0.03204 0.02820 -0.1151 0.9232 0.0225
-8.250 -0.2709 0.02990 0.02585 -0.1147 0.9178 0.0226
-8.000 -0.2545 0.02830 0.02408 -0.1137 0.9106 0.0227
-7.750 -0.2352 0.02682 0.02244 -0.1131 0.9026 0.0229
-7.500 -0.2156 0.02560 0.02107 -0.1123 0.8935 0.0231
-7.250 -0.1938 0.02436 0.01964 -0.1118 0.8843 0.0234
-7.000 -0.1755 0.02312 0.01819 -0.1105 0.8741 0.0237
-6.750 -0.1552 0.02176 0.01657 -0.1094 0.8652 0.0239
-6.500 -0.1350 0.02058 0.01516 -0.1082 0.8555 0.0240
-6.250 -0.1133 0.01953 0.01390 -0.1072 0.8467 0.0242
-6.000 -0.0908 0.01859 0.01275 -0.1063 0.8365 0.0244
-5.750 -0.0684 0.01777 0.01173 -0.1052 0.8250 0.0246
-5.500 -0.0451 0.01703 0.01080 -0.1043 0.8134 0.0247
-5.250 -0.0214 0.01636 0.00996 -0.1034 0.8023 0.0249
-5.000 0.0023 0.01576 0.00922 -0.1026 0.7909 0.0251
-4.750 0.0262 0.01522 0.00854 -0.1017 0.7776 0.0252
-4.500 0.0499 0.01476 0.00794 -0.1007 0.7604 0.0254
-4.250 0.0728 0.01444 0.00744 -0.0996 0.7377 0.0257
-4.000 0.0946 0.01422 0.00702 -0.0981 0.7076 0.0260
-3.750 0.1154 0.01402 0.00662 -0.0965 0.6786 0.0261
-3.500 0.1368 0.01381 0.00624 -0.0951 0.6566 0.0262
-3.250 0.1587 0.01336 0.00570 -0.0938 0.6402 0.0264
-3.000 0.1812 0.01300 0.00527 -0.0927 0.6265 0.0266
-2.750 0.2039 0.01273 0.00494 -0.0916 0.6143 0.0269
-2.250 0.2503 0.01231 0.00442 -0.0896 0.5910 0.0274
-2.000 0.2737 0.01214 0.00420 -0.0886 0.5804 0.0277
-1.750 0.2971 0.01199 0.00401 -0.0877 0.5688 0.0281
-1.500 0.3208 0.01185 0.00383 -0.0868 0.5566 0.0284
-1.250 0.3439 0.01174 0.00367 -0.0857 0.5429 0.0287
-1.000 0.3668 0.01167 0.00353 -0.0846 0.5268 0.0291
-0.750 0.3890 0.01163 0.00341 -0.0834 0.5074 0.0295
-0.500 0.4104 0.01165 0.00333 -0.0821 0.4855 0.0301
-0.250 0.4319 0.01171 0.00328 -0.0807 0.4649 0.0306
0.000 0.4535 0.01172 0.00319 -0.0795 0.4475 0.0312
0.250 0.4753 0.01175 0.00314 -0.0782 0.4314 0.0318
0.750 0.5206 0.01187 0.00310 -0.0761 0.4051 0.0333
1.000 0.5439 0.01193 0.00310 -0.0752 0.3962 0.0342
1.250 0.5678 0.01197 0.00310 -0.0744 0.3888 0.0353
1.500 0.5911 0.01204 0.00313 -0.0735 0.3826 0.0369
1.750 0.6154 0.01206 0.00316 -0.0727 0.3771 0.0407
2.000 0.6360 0.01175 0.00324 -0.0715 0.3717 0.1870
2.250 0.6586 0.01176 0.00335 -0.0705 0.3664 0.2342
2.500 0.6823 0.01178 0.00345 -0.0697 0.3618 0.2680
2.750 0.7055 0.01182 0.00356 -0.0689 0.3563 0.3003
3.000 0.7277 0.01191 0.00367 -0.0678 0.3505 0.3265
3.250 0.7506 0.01193 0.00377 -0.0669 0.3454 0.3613
3.500 0.7653 0.01120 0.00386 -0.0646 0.3411 0.6854
4.000 0.8815 0.01153 0.00483 -0.0777 0.3306 0.9859
4.250 0.9229 0.01174 0.00503 -0.0809 0.3268 0.9914
4.500 0.9615 0.01195 0.00521 -0.0835 0.3227 0.9949
4.750 0.9992 0.01218 0.00539 -0.0860 0.3176 0.9977
5.000 1.0357 0.01239 0.00558 -0.0881 0.3128 1.0000
5.250 1.0528 0.01251 0.00571 -0.0861 0.3097 1.0000
5.500 1.0677 0.01264 0.00583 -0.0835 0.3065 1.0000
5.750 1.0805 0.01278 0.00597 -0.0805 0.3030 1.0000
6.000 1.0928 0.01294 0.00612 -0.0774 0.2995 1.0000
6.250 1.1078 0.01308 0.00627 -0.0749 0.2966 1.0000
6.500 1.1235 0.01322 0.00642 -0.0726 0.2922 1.0000
6.750 1.1383 0.01340 0.00660 -0.0701 0.2866 1.0000
7.000 1.1533 0.01362 0.00679 -0.0678 0.2808 1.0000
7.250 1.1697 0.01382 0.00699 -0.0657 0.2734 1.0000
7.500 1.1846 0.01409 0.00723 -0.0634 0.2641 1.0000
7.750 1.1994 0.01439 0.00748 -0.0612 0.2529 1.0000
8.000 1.2150 0.01470 0.00776 -0.0591 0.2413 1.0000
8.250 1.2285 0.01514 0.00811 -0.0568 0.2245 1.0000
8.500 1.2397 0.01573 0.00859 -0.0542 0.2021 1.0000
8.750 1.2512 0.01636 0.00911 -0.0517 0.1857 1.0000
9.000 1.2647 0.01693 0.00963 -0.0496 0.1762 1.0000
9.250 1.2779 0.01754 0.01020 -0.0476 0.1679 1.0000
9.500 1.2918 0.01812 0.01078 -0.0457 0.1597 1.0000
9.750 1.3040 0.01883 0.01145 -0.0436 0.1518 1.0000
10.000 1.3196 0.01937 0.01200 -0.0421 0.1451 1.0000
10.250 1.3315 0.02012 0.01272 -0.0401 0.1365 1.0000
10.500 1.3434 0.02091 0.01346 -0.0383 0.1244 1.0000
10.750 1.3420 0.02253 0.01484 -0.0349 0.0891 1.0000
11.000 1.3272 0.02509 0.01717 -0.0303 0.0474 1.0000
11.250 1.3178 0.02747 0.01946 -0.0267 0.0204 1.0000
11.500 1.3252 0.02878 0.02081 -0.0250 0.0177 1.0000
11.750 1.3340 0.03002 0.02212 -0.0236 0.0165 1.0000
12.000 1.3417 0.03139 0.02356 -0.0222 0.0157 1.0000
12.250 1.3480 0.03292 0.02517 -0.0208 0.0149 1.0000
12.500 1.3532 0.03461 0.02694 -0.0194 0.0143 1.0000
12.750 1.3599 0.03624 0.02866 -0.0184 0.0139 1.0000
13.000 1.3653 0.03804 0.03054 -0.0174 0.0135 1.0000
13.250 1.3696 0.04003 0.03263 -0.0165 0.0131 1.0000
13.500 1.3727 0.04224 0.03493 -0.0158 0.0127 1.0000
13.750 1.3745 0.04468 0.03745 -0.0152 0.0123 1.0000
14.000 1.3746 0.04739 0.04026 -0.0148 0.0120 1.0000
14.250 1.3723 0.05046 0.04343 -0.0145 0.0117 1.0000
14.500 1.3674 0.05393 0.04700 -0.0143 0.0114 1.0000
14.750 1.3619 0.05756 0.05075 -0.0144 0.0112 1.0000
15.000 1.3583 0.06101 0.05431 -0.0145 0.0111 1.0000
15.250 1.3533 0.06473 0.05814 -0.0148 0.0109 1.0000
15.500 1.3471 0.06869 0.06221 -0.0152 0.0108 1.0000
15.750 1.3396 0.07291 0.06655 -0.0158 0.0107 1.0000
16.000 1.3310 0.07735 0.07110 -0.0166 0.0105 1.0000
16.250 1.3218 0.08195 0.07581 -0.0175 0.0104 1.0000
16.500 1.3120 0.08672 0.08070 -0.0185 0.0103 1.0000
16.750 1.3018 0.09160 0.08569 -0.0196 0.0102 1.0000
17.000 1.2912 0.09654 0.09074 -0.0208 0.0101 1.0000
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