GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il) Reynolds number: 500,000 Max Cl/Cd: 116.58 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe225-il-500000.txt Download as CSV file: xf-goe225-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.0130 0.08825 0.08536 -0.0996 0.8788 0.0413
-8.750 -0.0022 0.08602 0.08311 -0.1007 0.8757 0.0423
-8.000 -0.0109 0.02247 0.01813 -0.1947 0.8610 0.0371
-7.750 0.0237 0.02031 0.01561 -0.1986 0.8584 0.0373
-7.500 0.0565 0.01886 0.01389 -0.2010 0.8560 0.0377
-7.250 0.0885 0.01773 0.01257 -0.2028 0.8534 0.0381
-7.000 0.1200 0.01688 0.01155 -0.2041 0.8503 0.0387
-6.750 0.1512 0.01617 0.01069 -0.2052 0.8471 0.0392
-6.500 0.1822 0.01552 0.00989 -0.2061 0.8440 0.0395
-6.250 0.2137 0.01460 0.00884 -0.2072 0.8414 0.0400
-6.000 0.2448 0.01389 0.00806 -0.2081 0.8389 0.0407
-5.750 0.2757 0.01342 0.00756 -0.2090 0.8363 0.0414
-5.500 0.3065 0.01300 0.00713 -0.2097 0.8336 0.0422
-5.250 0.3374 0.01263 0.00671 -0.2104 0.8304 0.0431
-5.000 0.3682 0.01228 0.00631 -0.2110 0.8272 0.0442
-4.750 0.3989 0.01200 0.00596 -0.2115 0.8241 0.0453
-4.500 0.4304 0.01162 0.00553 -0.2123 0.8212 0.0473
-4.250 0.4610 0.01136 0.00527 -0.2129 0.8180 0.0492
-4.000 0.4915 0.01112 0.00500 -0.2133 0.8141 0.0517
-3.750 0.5222 0.01084 0.00472 -0.2138 0.8100 0.0567
-3.500 0.5529 0.01061 0.00452 -0.2143 0.8063 0.0691
-3.250 0.5825 0.01060 0.00452 -0.2144 0.8027 0.0875
-3.000 0.6118 0.01051 0.00447 -0.2146 0.7981 0.0977
-2.750 0.6413 0.01040 0.00434 -0.2148 0.7930 0.1045
-2.500 0.6711 0.01027 0.00417 -0.2150 0.7883 0.1105
-2.250 0.7005 0.01021 0.00407 -0.2152 0.7834 0.1150
-2.000 0.7302 0.01001 0.00390 -0.2155 0.7772 0.1214
-1.750 0.7598 0.00986 0.00373 -0.2157 0.7712 0.1275
-1.500 0.7891 0.00975 0.00360 -0.2158 0.7641 0.1331
-1.250 0.8186 0.00957 0.00345 -0.2161 0.7559 0.1429
-1.000 0.8480 0.00941 0.00333 -0.2163 0.7469 0.1586
-0.750 0.8775 0.00918 0.00326 -0.2166 0.7360 0.2252
-0.500 0.9059 0.00911 0.00326 -0.2166 0.7208 0.2703
-0.250 0.9336 0.00911 0.00322 -0.2164 0.7005 0.2904
0.000 0.9600 0.00921 0.00318 -0.2159 0.6726 0.3043
0.250 0.9852 0.00944 0.00323 -0.2152 0.6417 0.3164
0.500 1.0104 0.00971 0.00335 -0.2146 0.6170 0.3278
0.750 1.0361 0.00997 0.00350 -0.2142 0.5987 0.3398
1.000 1.0622 0.01020 0.00366 -0.2138 0.5849 0.3502
1.250 1.0883 0.01042 0.00382 -0.2134 0.5732 0.3611
1.500 1.1151 0.01059 0.00397 -0.2132 0.5636 0.3743
1.750 1.1413 0.01082 0.00416 -0.2129 0.5550 0.3876
2.000 1.1683 0.01095 0.00432 -0.2127 0.5466 0.4032
2.500 1.2204 0.01134 0.00471 -0.2120 0.5284 0.4407
2.750 1.2459 0.01159 0.00492 -0.2115 0.5206 0.4622
3.000 1.2726 0.01172 0.00511 -0.2113 0.5143 0.4827
3.250 1.2986 0.01190 0.00531 -0.2109 0.5079 0.5027
3.500 1.3238 0.01216 0.00555 -0.2104 0.5019 0.5219
3.750 1.3504 0.01226 0.00573 -0.2102 0.4966 0.5398
4.000 1.3761 0.01244 0.00593 -0.2098 0.4906 0.5559
4.250 1.4008 0.01269 0.00617 -0.2092 0.4849 0.5716
4.500 1.4269 0.01280 0.00636 -0.2089 0.4799 0.5876
4.750 1.4522 0.01295 0.00657 -0.2085 0.4742 0.6042
5.000 1.4763 0.01318 0.00681 -0.2078 0.4685 0.6233
5.250 1.5014 0.01329 0.00704 -0.2074 0.4627 0.6502
5.500 1.5225 0.01306 0.00727 -0.2060 0.4568 0.8586
5.750 1.5438 0.01328 0.00747 -0.2047 0.4511 1.0000
6.000 1.5678 0.01347 0.00769 -0.2041 0.4446 1.0000
6.250 1.5898 0.01374 0.00794 -0.2030 0.4367 1.0000
6.500 1.6114 0.01401 0.00821 -0.2019 0.4285 1.0000
6.750 1.6317 0.01431 0.00849 -0.2005 0.4198 1.0000
7.000 1.6518 0.01461 0.00880 -0.1991 0.4117 1.0000
7.250 1.6693 0.01496 0.00914 -0.1973 0.4028 1.0000
7.500 1.6868 0.01532 0.00951 -0.1954 0.3938 1.0000
7.750 1.7023 0.01580 0.00996 -0.1933 0.3840 1.0000
8.000 1.7199 0.01623 0.01040 -0.1916 0.3728 1.0000
8.250 1.7348 0.01679 0.01094 -0.1895 0.3600 1.0000
8.500 1.7488 0.01744 0.01155 -0.1873 0.3466 1.0000
8.750 1.7618 0.01817 0.01223 -0.1850 0.3317 1.0000
9.000 1.7731 0.01903 0.01303 -0.1826 0.3137 1.0000
9.250 1.7827 0.02005 0.01396 -0.1800 0.2940 1.0000
9.500 1.7914 0.02116 0.01498 -0.1774 0.2758 1.0000
9.750 1.8007 0.02227 0.01603 -0.1750 0.2602 1.0000
10.000 1.8103 0.02340 0.01711 -0.1727 0.2465 1.0000
10.250 1.8198 0.02456 0.01823 -0.1704 0.2346 1.0000
10.500 1.8282 0.02582 0.01946 -0.1681 0.2236 1.0000
10.750 1.8379 0.02701 0.02065 -0.1660 0.2134 1.0000
11.000 1.8472 0.02826 0.02188 -0.1639 0.2038 1.0000
11.250 1.8536 0.02973 0.02332 -0.1616 0.1939 1.0000
11.500 1.8624 0.03105 0.02467 -0.1597 0.1842 1.0000
11.750 1.8693 0.03254 0.02615 -0.1575 0.1741 1.0000
12.000 1.8735 0.03427 0.02785 -0.1552 0.1631 1.0000
12.250 1.8759 0.03618 0.02973 -0.1529 0.1501 1.0000
12.500 1.8761 0.03835 0.03184 -0.1504 0.1330 1.0000
12.750 1.8665 0.04146 0.03480 -0.1473 0.1069 1.0000
13.250 1.8295 0.04993 0.04298 -0.1408 0.0597 1.0000
13.500 1.8233 0.05322 0.04631 -0.1388 0.0549 1.0000
13.750 1.8195 0.05639 0.04955 -0.1372 0.0512 1.0000
14.000 1.8162 0.05961 0.05286 -0.1358 0.0483 1.0000
14.250 1.8087 0.06344 0.05676 -0.1345 0.0458 1.0000
14.500 1.8060 0.06678 0.06020 -0.1335 0.0436 1.0000
14.750 1.8030 0.07024 0.06375 -0.1326 0.0414 1.0000
15.000 1.7953 0.07440 0.06799 -0.1319 0.0395 1.0000
15.250 1.7870 0.07875 0.07244 -0.1314 0.0378 1.0000
15.500 1.7848 0.08228 0.07608 -0.1310 0.0360 1.0000
15.750 1.7788 0.08639 0.08026 -0.1307 0.0345 1.0000
16.000 1.7683 0.09120 0.08515 -0.1307 0.0332 1.0000
16.250 1.7597 0.09578 0.08983 -0.1307 0.0319 1.0000
16.500 1.7559 0.09968 0.09383 -0.1308 0.0306 1.0000
16.750 1.7499 0.10390 0.09814 -0.1310 0.0295 1.0000
17.000 1.7409 0.10862 0.10293 -0.1314 0.0286 1.0000
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Polar data table (+)
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