GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.95 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe233-il-1000000-n5.txt Download as CSV file: xf-goe233-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 233 (MVA CA4) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4816 0.06024 0.05765 -0.0932 0.8745 0.0169
-11.500 -0.4816 0.05528 0.05259 -0.0987 0.8632 0.0170
-11.250 -0.4718 0.05071 0.04791 -0.1052 0.8544 0.0171
-11.000 -0.4561 0.04660 0.04370 -0.1119 0.8460 0.0173
-10.750 -0.4359 0.04261 0.03960 -0.1192 0.8389 0.0174
-10.500 -0.4110 0.03882 0.03570 -0.1271 0.8318 0.0176
-10.000 -0.3478 0.03197 0.02857 -0.1439 0.8190 0.0182
-9.750 -0.3106 0.02901 0.02545 -0.1524 0.8124 0.0185
-9.500 -0.2715 0.02638 0.02265 -0.1603 0.8068 0.0190
-9.250 -0.2319 0.02413 0.02024 -0.1673 0.8016 0.0194
-9.000 -0.1930 0.02226 0.01822 -0.1732 0.7960 0.0197
-8.750 -0.1551 0.02071 0.01650 -0.1781 0.7906 0.0199
-8.500 -0.1184 0.01931 0.01502 -0.1823 0.7855 0.0203
-8.250 -0.0828 0.01821 0.01384 -0.1857 0.7793 0.0206
-8.000 -0.0479 0.01725 0.01278 -0.1887 0.7731 0.0208
-7.750 -0.0131 0.01632 0.01178 -0.1915 0.7669 0.0211
-7.500 0.0210 0.01550 0.01086 -0.1939 0.7604 0.0214
-7.250 0.0546 0.01477 0.01003 -0.1960 0.7544 0.0217
-7.000 0.0879 0.01409 0.00927 -0.1979 0.7476 0.0220
-6.750 0.1205 0.01350 0.00858 -0.1995 0.7401 0.0224
-6.500 0.1529 0.01295 0.00796 -0.2009 0.7327 0.0227
-6.250 0.1848 0.01248 0.00739 -0.2022 0.7241 0.0230
-6.000 0.2164 0.01206 0.00688 -0.2033 0.7148 0.0232
-5.750 0.2476 0.01173 0.00644 -0.2042 0.7028 0.0234
-5.500 0.2786 0.01143 0.00604 -0.2050 0.6899 0.0235
-5.250 0.3094 0.01116 0.00568 -0.2058 0.6790 0.0237
-5.000 0.3417 0.01068 0.00510 -0.2070 0.6706 0.0241
-4.750 0.3732 0.01033 0.00469 -0.2080 0.6629 0.0245
-4.250 0.4347 0.00986 0.00409 -0.2093 0.6495 0.0253
-4.000 0.4652 0.00966 0.00382 -0.2099 0.6435 0.0257
-3.750 0.4955 0.00949 0.00359 -0.2103 0.6378 0.0261
-3.500 0.5259 0.00932 0.00337 -0.2108 0.6326 0.0264
-3.250 0.5560 0.00919 0.00319 -0.2112 0.6268 0.0268
-2.750 0.6157 0.00898 0.00288 -0.2118 0.6156 0.0275
-2.500 0.6453 0.00891 0.00276 -0.2121 0.6096 0.0278
-2.000 0.7048 0.00874 0.00250 -0.2126 0.5999 0.0291
-1.750 0.7343 0.00869 0.00241 -0.2128 0.5936 0.0300
-1.500 0.7633 0.00869 0.00235 -0.2130 0.5863 0.0312
-1.250 0.7927 0.00865 0.00229 -0.2131 0.5801 0.0322
-1.000 0.8219 0.00863 0.00225 -0.2133 0.5750 0.0342
-0.750 0.8515 0.00853 0.00218 -0.2136 0.5700 0.0636
-0.500 0.8807 0.00850 0.00216 -0.2137 0.5657 0.0749
-0.250 0.9099 0.00847 0.00214 -0.2139 0.5603 0.0847
0.000 0.9394 0.00835 0.00211 -0.2142 0.5544 0.1363
0.250 0.9684 0.00830 0.00211 -0.2144 0.5476 0.1606
0.500 0.9975 0.00822 0.00210 -0.2147 0.5384 0.2102
0.750 1.0261 0.00821 0.00216 -0.2148 0.5298 0.2542
1.000 1.0542 0.00830 0.00225 -0.2147 0.5202 0.2695
1.250 1.0824 0.00838 0.00232 -0.2146 0.5121 0.2775
1.500 1.1102 0.00851 0.00243 -0.2145 0.5026 0.2889
1.750 1.1379 0.00863 0.00254 -0.2144 0.4914 0.2969
2.000 1.1654 0.00878 0.00265 -0.2142 0.4802 0.3022
2.250 1.1926 0.00895 0.00277 -0.2140 0.4693 0.3060
2.500 1.2200 0.00910 0.00289 -0.2138 0.4584 0.3081
2.750 1.2471 0.00928 0.00303 -0.2136 0.4471 0.3104
3.000 1.2739 0.00947 0.00318 -0.2133 0.4361 0.3129
3.250 1.3009 0.00964 0.00334 -0.2131 0.4258 0.3160
3.500 1.3273 0.00986 0.00351 -0.2128 0.4139 0.3195
3.750 1.3535 0.01009 0.00370 -0.2124 0.4026 0.3226
4.000 1.3803 0.01025 0.00385 -0.2122 0.3938 0.3246
4.250 1.4065 0.01046 0.00405 -0.2118 0.3843 0.3281
4.500 1.4321 0.01072 0.00427 -0.2114 0.3702 0.3310
4.750 1.4566 0.01108 0.00454 -0.2108 0.3469 0.3330
5.000 1.4791 0.01161 0.00489 -0.2099 0.3126 0.3347
5.250 1.4993 0.01232 0.00537 -0.2086 0.2721 0.3363
5.500 1.5206 0.01290 0.00581 -0.2075 0.2455 0.3378
5.750 1.5439 0.01328 0.00614 -0.2067 0.2331 0.3392
6.000 1.5668 0.01367 0.00648 -0.2059 0.2218 0.3404
6.250 1.5897 0.01403 0.00682 -0.2050 0.2123 0.3423
6.500 1.6128 0.01436 0.00714 -0.2042 0.2048 0.3441
6.750 1.6362 0.01464 0.00745 -0.2034 0.1994 0.3462
7.000 1.6583 0.01501 0.00780 -0.2024 0.1929 0.3483
7.250 1.6811 0.01530 0.00812 -0.2015 0.1875 0.3503
7.500 1.7026 0.01566 0.00847 -0.2004 0.1802 0.3521
7.750 1.7229 0.01607 0.00887 -0.1992 0.1707 0.3537
8.000 1.7400 0.01666 0.00937 -0.1974 0.1535 0.3550
8.500 1.7412 0.01922 0.01148 -0.1883 0.0834 0.3570
8.750 1.7480 0.02028 0.01248 -0.1850 0.0672 0.3586
9.000 1.7567 0.02129 0.01345 -0.1821 0.0557 0.3601
9.250 1.7664 0.02227 0.01441 -0.1795 0.0479 0.3619
9.500 1.7767 0.02325 0.01539 -0.1772 0.0424 0.3638
9.750 1.7887 0.02414 0.01632 -0.1751 0.0392 0.3657
10.000 1.7994 0.02517 0.01736 -0.1729 0.0360 0.3674
10.250 1.8107 0.02618 0.01841 -0.1709 0.0339 0.3690
10.500 1.8222 0.02721 0.01949 -0.1690 0.0323 0.3704
10.750 1.8324 0.02837 0.02068 -0.1671 0.0306 0.3716
11.000 1.8416 0.02965 0.02200 -0.1651 0.0288 0.3733
11.250 1.8520 0.03085 0.02326 -0.1634 0.0276 0.3751
11.500 1.8616 0.03216 0.02463 -0.1616 0.0263 0.3770
11.750 1.8700 0.03361 0.02612 -0.1598 0.0250 0.3791
12.000 1.8770 0.03520 0.02776 -0.1580 0.0237 0.3812
12.250 1.8850 0.03672 0.02934 -0.1563 0.0226 0.3832
12.500 1.8920 0.03837 0.03105 -0.1547 0.0213 0.3849
12.750 1.8974 0.04021 0.03293 -0.1530 0.0199 0.3864
13.000 1.9024 0.04212 0.03489 -0.1513 0.0186 0.3879
13.250 1.9073 0.04407 0.03691 -0.1498 0.0174 0.3898
13.500 1.9109 0.04622 0.03912 -0.1483 0.0163 0.3917
13.750 1.9138 0.04852 0.04147 -0.1469 0.0153 0.3937
14.000 1.9175 0.05077 0.04380 -0.1456 0.0146 0.3958
14.250 1.9200 0.05319 0.04629 -0.1444 0.0138 0.3979
14.500 1.9212 0.05580 0.04897 -0.1432 0.0130 0.4001
14.750 1.9213 0.05862 0.05185 -0.1421 0.0123 0.4021
15.000 1.9227 0.06134 0.05465 -0.1411 0.0118 0.4045
15.250 1.9233 0.06417 0.05757 -0.1402 0.0114 0.4071
15.500 1.9229 0.06716 0.06064 -0.1393 0.0109 0.4096
15.750 1.9209 0.07039 0.06396 -0.1386 0.0104 0.4120
16.000 1.9180 0.07381 0.06745 -0.1379 0.0099 0.4145
16.250 1.9148 0.07730 0.07102 -0.1373 0.0095 0.4168
16.500 1.9133 0.08059 0.07441 -0.1368 0.0093 0.4196
16.750 1.9102 0.08412 0.07804 -0.1364 0.0091 0.4228
17.000 1.9062 0.08783 0.08184 -0.1362 0.0088 0.4263
17.250 1.9019 0.09161 0.08572 -0.1360 0.0086 0.4300
17.750 1.8913 0.09960 0.09390 -0.1360 0.0081 0.4383
18.000 1.8846 0.10385 0.09825 -0.1363 0.0079 0.4436
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