USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 27 AIRFOIL (usa27-il) Reynolds number: 500,000 Max Cl/Cd: 95.42 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa27-il-500000.txt Download as CSV file: xf-usa27-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3138 0.11868 0.11644 -0.0305 1.0000 0.0214
-10.250 -0.3209 0.11607 0.11386 -0.0303 1.0000 0.0221
-10.000 -0.3311 0.11307 0.11090 -0.0317 0.9997 0.0224
-9.750 -0.3225 0.10792 0.10574 -0.0375 0.9978 0.0225
-9.500 -0.3129 0.10283 0.10065 -0.0429 0.9959 0.0225
-9.250 -0.3007 0.09891 0.09674 -0.0432 0.9950 0.0228
-9.000 -0.2838 0.09595 0.09378 -0.0450 0.9939 0.0231
-8.750 -0.2691 0.09281 0.09064 -0.0474 0.9913 0.0236
-8.500 -0.2547 0.08928 0.08710 -0.0511 0.9886 0.0242
-8.250 -0.2398 0.08528 0.08310 -0.0559 0.9860 0.0249
-8.000 -0.2237 0.08061 0.07842 -0.0626 0.9837 0.0260
-7.750 -0.2087 0.07172 0.06948 -0.0797 0.9732 0.0273
-7.250 -0.1789 0.06088 0.05854 -0.0897 0.9632 0.0279
-7.000 -0.1522 0.05815 0.05579 -0.0931 0.9610 0.0284
-6.750 -0.1230 0.05472 0.05231 -0.0979 0.9588 0.0291
-6.500 -0.1059 0.05135 0.04886 -0.1000 0.9506 0.0300
-6.250 -0.0757 0.04122 0.03815 -0.1087 0.9445 0.0333
-6.000 -0.0718 0.03539 0.03211 -0.1081 0.9348 0.0340
-5.750 -0.0463 0.03346 0.03018 -0.1092 0.9302 0.0346
-5.500 -0.0277 0.03208 0.02875 -0.1085 0.9222 0.0353
-5.250 -0.0045 0.03011 0.02664 -0.1088 0.9162 0.0367
-5.000 0.0182 0.02887 0.02486 -0.1075 0.9077 0.0405
-4.750 0.0330 0.02437 0.02006 -0.1068 0.9005 0.0422
-4.500 0.0542 0.02307 0.01873 -0.1060 0.8913 0.0432
-4.250 0.0801 0.02185 0.01738 -0.1060 0.8838 0.0450
-4.000 0.1054 0.02210 0.01736 -0.1048 0.8734 0.0492
-3.750 0.1237 0.01926 0.01428 -0.1038 0.8639 0.0523
-3.500 0.1494 0.01842 0.01339 -0.1036 0.8539 0.0551
-3.250 0.1716 0.01765 0.01232 -0.1023 0.8414 0.0629
-3.000 0.1958 0.01669 0.01136 -0.1018 0.8285 0.0661
-2.750 0.2245 0.01838 0.01288 -0.1011 0.8137 0.0733
-2.000 0.2985 0.01240 0.00596 -0.0972 0.7639 0.0451
-1.750 0.3233 0.01180 0.00516 -0.0960 0.7411 0.0428
-1.250 0.3708 0.01155 0.00457 -0.0937 0.6891 0.0410
-0.750 0.4169 0.01100 0.00380 -0.0914 0.6517 0.0406
-0.250 0.4641 0.01062 0.00327 -0.0894 0.6243 0.0409
0.000 0.4877 0.01042 0.00302 -0.0884 0.6121 0.0413
0.250 0.5114 0.01030 0.00284 -0.0875 0.5995 0.0419
0.500 0.5350 0.01022 0.00270 -0.0866 0.5852 0.0437
0.750 0.5587 0.01020 0.00261 -0.0856 0.5696 0.0451
1.000 0.5827 0.01021 0.00255 -0.0847 0.5532 0.0463
1.250 0.6066 0.01023 0.00249 -0.0839 0.5364 0.0483
1.500 0.6304 0.01027 0.00247 -0.0830 0.5185 0.0538
1.750 0.6510 0.00999 0.00255 -0.0816 0.5003 0.2133
2.000 0.6728 0.00995 0.00267 -0.0805 0.4823 0.3079
2.250 0.6908 0.00954 0.00274 -0.0788 0.4662 0.5253
2.500 0.7977 0.00926 0.00337 -0.0961 0.4402 0.9957
2.750 0.8422 0.00949 0.00347 -0.1000 0.4265 1.0000
3.000 0.8627 0.00970 0.00358 -0.0986 0.4168 1.0000
3.250 0.8846 0.00984 0.00369 -0.0974 0.4086 1.0000
3.750 0.9268 0.01018 0.00394 -0.0948 0.3947 1.0000
4.000 0.9473 0.01037 0.00408 -0.0933 0.3880 1.0000
4.250 0.9685 0.01053 0.00422 -0.0920 0.3824 1.0000
4.500 0.9896 0.01068 0.00436 -0.0907 0.3765 1.0000
4.750 1.0095 0.01090 0.00452 -0.0892 0.3708 1.0000
5.000 1.0308 0.01103 0.00467 -0.0879 0.3657 1.0000
5.250 1.0516 0.01119 0.00483 -0.0865 0.3604 1.0000
5.500 1.0705 0.01143 0.00501 -0.0849 0.3542 1.0000
5.750 1.0917 0.01154 0.00515 -0.0836 0.3469 1.0000
6.000 1.1102 0.01176 0.00533 -0.0818 0.3394 1.0000
6.250 1.1310 0.01189 0.00548 -0.0805 0.3322 1.0000
6.500 1.1495 0.01211 0.00567 -0.0787 0.3247 1.0000
6.750 1.1699 0.01226 0.00585 -0.0774 0.3175 1.0000
7.000 1.1874 0.01251 0.00606 -0.0755 0.3083 1.0000
7.250 1.2073 0.01267 0.00624 -0.0740 0.2979 1.0000
7.500 1.2252 0.01291 0.00645 -0.0722 0.2852 1.0000
7.750 1.2416 0.01318 0.00669 -0.0701 0.2698 1.0000
8.000 1.2564 0.01355 0.00696 -0.0678 0.2494 1.0000
8.250 1.2676 0.01417 0.00738 -0.0650 0.2125 1.0000
8.500 1.2745 0.01509 0.00804 -0.0617 0.1772 1.0000
8.750 1.2850 0.01589 0.00869 -0.0590 0.1550 1.0000
9.000 1.2962 0.01666 0.00935 -0.0564 0.1325 1.0000
9.250 1.2920 0.01836 0.01060 -0.0518 0.0723 1.0000
9.500 1.2852 0.02026 0.01224 -0.0469 0.0247 1.0000
9.750 1.2966 0.02110 0.01313 -0.0448 0.0219 1.0000
10.000 1.3085 0.02193 0.01404 -0.0427 0.0202 1.0000
10.250 1.3206 0.02276 0.01496 -0.0409 0.0193 1.0000
10.500 1.3309 0.02373 0.01604 -0.0389 0.0183 1.0000
10.750 1.3393 0.02486 0.01726 -0.0368 0.0176 1.0000
11.000 1.3448 0.02624 0.01874 -0.0345 0.0170 1.0000
11.250 1.3466 0.02795 0.02056 -0.0321 0.0164 1.0000
11.500 1.3465 0.02988 0.02261 -0.0298 0.0161 1.0000
11.750 1.3516 0.03151 0.02433 -0.0281 0.0158 1.0000
12.000 1.3546 0.03337 0.02631 -0.0265 0.0156 1.0000
12.250 1.3559 0.03550 0.02854 -0.0251 0.0153 1.0000
12.500 1.3558 0.03787 0.03101 -0.0239 0.0150 1.0000
12.750 1.3542 0.04052 0.03376 -0.0229 0.0147 1.0000
13.000 1.3515 0.04345 0.03681 -0.0222 0.0144 1.0000
13.250 1.3479 0.04667 0.04013 -0.0218 0.0141 1.0000
13.500 1.3428 0.05019 0.04376 -0.0217 0.0139 1.0000
13.750 1.3365 0.05398 0.04765 -0.0218 0.0136 1.0000
14.000 1.3290 0.05800 0.05178 -0.0220 0.0135 1.0000
14.250 1.3206 0.06219 0.05607 -0.0224 0.0133 1.0000
14.500 1.3118 0.06650 0.06046 -0.0228 0.0132 1.0000
14.750 1.3029 0.07087 0.06491 -0.0233 0.0131 1.0000
15.000 1.2944 0.07514 0.06926 -0.0238 0.0130 1.0000
15.250 1.2872 0.07912 0.07329 -0.0240 0.0128 1.0000
15.500 1.2829 0.08235 0.07654 -0.0236 0.0127 1.0000
15.750 1.2839 0.08500 0.07922 -0.0232 0.0125 1.0000
16.000 1.2846 0.08820 0.08252 -0.0237 0.0124 1.0000
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