GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il) Reynolds number: 100,000 Max Cl/Cd: 59.28 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe225-il-100000.txt Download as CSV file: xf-goe225-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 225 (MVA H.35) 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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2323 0.11368 0.10920 -0.0414 0.9642 0.1113
-6.750 -0.2415 0.11332 0.10888 -0.0467 0.9560 0.1147
-6.500 -0.2436 0.11095 0.10656 -0.0554 0.9446 0.1160
-6.250 -0.2163 0.10572 0.10130 -0.0518 0.9418 0.1176
-6.000 -0.1989 0.10275 0.09832 -0.0511 0.9349 0.1199
-5.750 -0.1798 0.09992 0.09548 -0.0536 0.9274 0.1244
-5.500 -0.1633 0.09660 0.09214 -0.0715 0.9133 0.1317
-5.250 -0.1424 0.09280 0.08834 -0.0670 0.9094 0.1336
-5.000 -0.1276 0.09038 0.08592 -0.0660 0.9006 0.1363
-4.750 -0.0983 0.08714 0.08264 -0.0715 0.8929 0.1428
-4.500 -0.0722 0.08299 0.07846 -0.0820 0.8816 0.1493
-4.250 -0.0091 0.07828 0.07359 -0.1009 0.8750 0.1640
-3.750 0.2096 0.04408 0.03779 -0.1676 0.8743 0.1043
-3.500 0.2576 0.04122 0.03452 -0.1742 0.8661 0.1072
-3.250 0.3200 0.03808 0.03065 -0.1826 0.8613 0.1125
-3.000 0.3801 0.03559 0.02768 -0.1893 0.8582 0.1200
-2.750 0.2108 0.05716 0.05209 -0.1314 0.8279 0.1882
-2.500 0.4641 0.03326 0.02513 -0.1948 0.8433 0.1539
-2.250 0.5157 0.03224 0.02401 -0.1987 0.8399 0.1817
-2.000 0.5408 0.03229 0.02414 -0.1981 0.8280 0.1998
-1.750 0.5863 0.03183 0.02375 -0.2006 0.8236 0.2250
-1.500 0.6195 0.03146 0.02337 -0.2012 0.8146 0.2394
-1.250 0.6602 0.03077 0.02264 -0.2029 0.8081 0.2577
-1.000 0.7081 0.02969 0.02151 -0.2055 0.8053 0.2847
-0.750 0.7313 0.02967 0.02161 -0.2044 0.7930 0.3130
-0.500 0.7736 0.02882 0.02089 -0.2058 0.7890 0.3633
-0.250 0.7978 0.02890 0.02102 -0.2047 0.7781 0.3960
0.000 0.8350 0.02839 0.02048 -0.2053 0.7727 0.4281
0.250 0.8758 0.02759 0.01971 -0.2063 0.7696 0.4522
0.500 0.8950 0.02785 0.01997 -0.2046 0.7566 0.4685
0.750 0.9356 0.02702 0.01912 -0.2057 0.7532 0.4910
1.000 0.9541 0.02735 0.01948 -0.2040 0.7407 0.5090
1.250 0.9945 0.02650 0.01858 -0.2052 0.7370 0.5339
1.500 1.0139 0.02677 0.01890 -0.2037 0.7252 0.5512
1.750 1.0532 0.02588 0.01800 -0.2048 0.7210 0.5731
2.000 1.0743 0.02612 0.01827 -0.2037 0.7100 0.5901
2.250 1.1139 0.02527 0.01736 -0.2051 0.7052 0.6114
2.500 1.1363 0.02547 0.01755 -0.2042 0.6952 0.6325
2.750 1.1729 0.02469 0.01678 -0.2051 0.6897 0.6612
3.000 1.1964 0.02473 0.01690 -0.2042 0.6805 0.6922
3.250 1.2293 0.02399 0.01629 -0.2045 0.6742 0.7451
3.500 1.2498 0.02378 0.01631 -0.2029 0.6655 1.0000
3.750 1.2860 0.02361 0.01597 -0.2042 0.6581 1.0000
4.000 1.3135 0.02389 0.01615 -0.2041 0.6489 1.0000
4.250 1.3493 0.02362 0.01572 -0.2050 0.6407 1.0000
4.500 1.3724 0.02406 0.01612 -0.2041 0.6301 1.0000
4.750 1.4109 0.02380 0.01565 -0.2054 0.6224 1.0000
5.000 1.4290 0.02451 0.01642 -0.2038 0.6116 1.0000
5.250 1.4607 0.02468 0.01648 -0.2042 0.6033 1.0000
5.500 1.4831 0.02523 0.01703 -0.2033 0.5935 1.0000
5.750 1.5103 0.02564 0.01741 -0.2030 0.5846 1.0000
6.000 1.5354 0.02610 0.01785 -0.2025 0.5753 1.0000
6.250 1.5587 0.02670 0.01846 -0.2017 0.5661 1.0000
6.500 1.5861 0.02709 0.01880 -0.2014 0.5570 1.0000
6.750 1.6053 0.02783 0.01963 -0.2000 0.5472 1.0000
7.000 1.6361 0.02812 0.01983 -0.2003 0.5382 1.0000
7.250 1.6502 0.02899 0.02084 -0.1981 0.5278 1.0000
7.500 1.6833 0.02927 0.02101 -0.1987 0.5190 1.0000
7.750 1.6939 0.03016 0.02210 -0.1959 0.5081 1.0000
8.000 1.7180 0.03069 0.02262 -0.1952 0.4982 1.0000
8.250 1.7384 0.03120 0.02318 -0.1938 0.4875 1.0000
8.500 1.7518 0.03198 0.02408 -0.1914 0.4763 1.0000
8.750 1.7780 0.03223 0.02426 -0.1909 0.4655 1.0000
9.000 1.7892 0.03283 0.02497 -0.1880 0.4534 1.0000
9.250 1.7988 0.03351 0.02576 -0.1850 0.4414 1.0000
9.500 1.8163 0.03382 0.02606 -0.1831 0.4297 1.0000
9.750 1.8305 0.03416 0.02639 -0.1806 0.4177 1.0000
10.000 1.8299 0.03507 0.02745 -0.1761 0.4060 1.0000
10.250 1.8373 0.03565 0.02804 -0.1727 0.3951 1.0000
10.500 1.8490 0.03609 0.02846 -0.1700 0.3843 1.0000
10.750 1.8436 0.03737 0.02991 -0.1651 0.3740 1.0000
11.000 1.8536 0.03811 0.03064 -0.1625 0.3642 1.0000
11.250 1.8562 0.03921 0.03182 -0.1591 0.3542 1.0000
11.500 1.8571 0.04053 0.03323 -0.1556 0.3446 1.0000
11.750 1.8680 0.04121 0.03385 -0.1533 0.3345 1.0000
12.000 1.8587 0.04317 0.03601 -0.1491 0.3249 1.0000
12.250 1.8621 0.04447 0.03733 -0.1463 0.3155 1.0000
12.500 1.8607 0.04612 0.03906 -0.1433 0.3061 1.0000
12.750 1.8583 0.04801 0.04107 -0.1404 0.2972 1.0000
13.000 1.8618 0.04941 0.04245 -0.1380 0.2879 1.0000
13.250 1.8506 0.05213 0.04539 -0.1348 0.2789 1.0000
13.500 1.8480 0.05412 0.04739 -0.1323 0.2693 1.0000
13.750 1.8371 0.05701 0.05044 -0.1296 0.2600 1.0000
14.000 1.8281 0.05989 0.05342 -0.1272 0.2504 1.0000
14.250 1.8219 0.06254 0.05606 -0.1252 0.2402 1.0000
14.500 1.8050 0.06678 0.06055 -0.1233 0.2305 1.0000
14.750 1.7914 0.07078 0.06464 -0.1219 0.2196 1.0000
15.000 1.7760 0.07524 0.06915 -0.1208 0.2078 1.0000
15.250 1.7571 0.08048 0.07445 -0.1202 0.1948 1.0000
15.500 1.7348 0.08666 0.08075 -0.1203 0.1809 1.0000
15.750 1.7116 0.09321 0.08735 -0.1208 0.1657 1.0000
16.000 1.6871 0.10029 0.09448 -0.1218 0.1491 1.0000
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Polar data table (+)
Polar graphs
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