GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Reynolds number: 200,000 Max Cl/Cd: 78.59 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe242-il-200000.txt Download as CSV file: xf-goe242-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 242 (MVA PR.2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.0635 0.09396 0.09059 -0.0995 0.8944 0.0539
-10.250 0.0738 0.09177 0.08837 -0.0987 0.8836 0.0563
-10.000 0.0763 0.08894 0.08549 -0.0991 0.8745 0.0592
-9.750 0.0583 0.08503 0.08160 -0.1042 0.8642 0.0621
-9.500 0.0627 0.08067 0.07721 -0.1037 0.8547 0.0633
-9.250 0.0800 0.07885 0.07532 -0.1013 0.8429 0.0650
-9.000 0.0897 0.07656 0.07300 -0.1008 0.8306 0.0674
-8.750 0.0921 0.07349 0.06989 -0.1018 0.8197 0.0711
-8.500 0.0634 0.06773 0.06413 -0.1110 0.8105 0.0743
-8.250 0.0888 0.06548 0.06183 -0.1055 0.7980 0.0767
-8.000 0.0078 0.07178 0.06814 -0.1184 0.8262 0.0747
-7.750 0.0355 0.07212 0.06841 -0.1101 0.8147 0.0766
-7.500 0.0516 0.07093 0.06715 -0.1084 0.8028 0.0792
-7.250 0.0377 0.05891 0.05509 -0.1326 0.7909 0.0888
-7.000 0.0572 0.06214 0.05830 -0.1193 0.7788 0.0904
-6.750 0.0761 0.06220 0.05829 -0.1156 0.7671 0.0945
-6.500 0.0870 0.05468 0.05072 -0.1297 0.7575 0.1055
-6.250 0.1052 0.05476 0.05074 -0.1261 0.7466 0.1095
-6.000 0.2281 0.02621 0.01953 -0.1928 0.7389 0.0627
-5.750 0.2610 0.02385 0.01693 -0.1946 0.7300 0.0614
-5.500 0.2949 0.02192 0.01475 -0.1965 0.7214 0.0602
-5.250 0.3280 0.02064 0.01321 -0.1977 0.7139 0.0599
-5.000 0.3605 0.01989 0.01225 -0.1988 0.7066 0.0613
-4.750 0.3920 0.01913 0.01133 -0.1995 0.6998 0.0618
-4.500 0.4231 0.01847 0.01053 -0.2001 0.6942 0.0621
-4.250 0.4535 0.01778 0.00984 -0.2006 0.6878 0.0629
-4.000 0.4855 0.01710 0.00918 -0.2017 0.6825 0.0655
-3.750 0.5186 0.01674 0.00879 -0.2030 0.6774 0.0681
-3.500 0.5525 0.01642 0.00845 -0.2045 0.6717 0.0704
-3.250 0.5870 0.01618 0.00807 -0.2061 0.6671 0.0733
-3.000 0.6232 0.01592 0.00767 -0.2082 0.6633 0.0792
-2.750 0.6579 0.01567 0.00746 -0.2100 0.6588 0.0946
-2.500 0.7005 0.01490 0.00766 -0.2144 0.6546 0.3957
-2.250 0.7281 0.01552 0.00818 -0.2138 0.6510 0.4386
-2.000 0.7540 0.01622 0.00883 -0.2127 0.6478 0.4577
-1.750 0.7792 0.01685 0.00948 -0.2117 0.6440 0.4733
-1.500 0.8047 0.01732 0.00997 -0.2109 0.6402 0.4825
-1.250 0.8313 0.01774 0.01036 -0.2103 0.6369 0.4919
-1.000 0.8586 0.01814 0.01070 -0.2099 0.6341 0.5013
-0.750 0.8830 0.01869 0.01124 -0.2087 0.6315 0.5104
-0.500 0.9104 0.01907 0.01163 -0.2086 0.6285 0.5222
-0.250 0.9335 0.01945 0.01210 -0.2073 0.6250 0.5277
0.000 0.9640 0.01959 0.01218 -0.2081 0.6218 0.5344
0.250 0.9937 0.01970 0.01222 -0.2086 0.6186 0.5394
0.500 1.0223 0.01989 0.01230 -0.2086 0.6148 0.5426
0.750 1.0494 0.01994 0.01241 -0.2088 0.6090 0.5462
1.000 1.0802 0.01991 0.01227 -0.2096 0.6030 0.5506
1.250 1.1121 0.01996 0.01214 -0.2106 0.5983 0.5548
1.500 1.1368 0.02010 0.01240 -0.2101 0.5934 0.5580
1.750 1.1642 0.02023 0.01256 -0.2101 0.5891 0.5623
2.000 1.1950 0.02030 0.01256 -0.2110 0.5854 0.5665
2.250 1.2279 0.02041 0.01251 -0.2124 0.5821 0.5697
2.500 1.2546 0.02055 0.01274 -0.2125 0.5784 0.5714
2.750 1.2815 0.02068 0.01295 -0.2126 0.5743 0.5735
3.000 1.3096 0.02079 0.01306 -0.2128 0.5703 0.5762
3.250 1.3397 0.02088 0.01309 -0.2134 0.5667 0.5796
3.500 1.3683 0.02106 0.01327 -0.2139 0.5627 0.5828
3.750 1.3956 0.02120 0.01347 -0.2142 0.5578 0.5858
4.000 1.4230 0.02127 0.01358 -0.2143 0.5536 0.5880
4.250 1.4523 0.02135 0.01362 -0.2147 0.5499 0.5906
4.500 1.4782 0.02156 0.01391 -0.2146 0.5454 0.5936
4.750 1.5036 0.02170 0.01415 -0.2145 0.5402 0.5973
5.000 1.5327 0.02176 0.01416 -0.2149 0.5355 0.6016
5.250 1.5603 0.02184 0.01425 -0.2150 0.5309 0.6045
5.500 1.5824 0.02199 0.01457 -0.2142 0.5245 0.6076
5.750 1.6096 0.02198 0.01457 -0.2142 0.5190 0.6112
6.000 1.6356 0.02210 0.01471 -0.2141 0.5133 0.6152
6.250 1.6583 0.02221 0.01494 -0.2134 0.5063 0.6187
6.500 1.6853 0.02218 0.01490 -0.2133 0.5006 0.6224
6.750 1.7046 0.02236 0.01525 -0.2120 0.4924 0.6267
7.000 1.7294 0.02233 0.01519 -0.2116 0.4847 0.6318
7.250 1.7463 0.02246 0.01549 -0.2098 0.4742 0.6355
7.500 1.7639 0.02251 0.01560 -0.2081 0.4628 0.6394
7.750 1.7793 0.02264 0.01574 -0.2060 0.4498 0.6438
8.000 1.7919 0.02292 0.01605 -0.2036 0.4351 0.6485
8.250 1.8005 0.02333 0.01653 -0.2005 0.4191 0.6523
8.500 1.8022 0.02393 0.01714 -0.1963 0.4030 0.6566
8.750 1.8052 0.02481 0.01798 -0.1927 0.3858 0.6617
9.000 1.8074 0.02595 0.01906 -0.1892 0.3696 0.6663
9.250 1.8089 0.02729 0.02034 -0.1860 0.3552 0.6708
9.500 1.8107 0.02878 0.02179 -0.1830 0.3428 0.6759
9.750 1.8126 0.03040 0.02336 -0.1803 0.3316 0.6810
10.000 1.8166 0.03195 0.02496 -0.1779 0.3215 0.6861
10.250 1.8193 0.03366 0.02665 -0.1756 0.3130 0.6923
10.500 1.8225 0.03540 0.02845 -0.1734 0.3040 0.6986
10.750 1.8248 0.03725 0.03034 -0.1713 0.2959 0.7056
11.000 1.8280 0.03911 0.03227 -0.1694 0.2885 0.7132
11.250 1.8299 0.04110 0.03431 -0.1674 0.2816 0.7214
11.500 1.8319 0.04317 0.03649 -0.1658 0.2740 0.7303
11.750 1.8314 0.04549 0.03884 -0.1639 0.2671 0.7406
12.000 1.8326 0.04779 0.04130 -0.1625 0.2593 0.7532
12.250 1.8307 0.05042 0.04400 -0.1610 0.2524 0.7712
12.500 1.8274 0.05284 0.04672 -0.1593 0.2442 0.9210
12.750 1.8241 0.05592 0.04981 -0.1581 0.2370 1.0000
13.000 1.8237 0.05893 0.05292 -0.1573 0.2285 1.0000
13.250 1.8197 0.06235 0.05638 -0.1565 0.2202 1.0000
13.500 1.8148 0.06595 0.06003 -0.1557 0.2108 1.0000
13.750 1.8074 0.06996 0.06408 -0.1551 0.1982 1.0000
14.000 1.7989 0.07415 0.06829 -0.1545 0.1843 1.0000
14.250 1.7851 0.07908 0.07317 -0.1540 0.1642 1.0000
14.500 1.7571 0.08587 0.07977 -0.1535 0.1265 1.0000
14.750 1.7261 0.09320 0.08689 -0.1533 0.0939 1.0000
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