GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.36 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe242-il-1000000.txt Download as CSV file: xf-goe242-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0664 0.09486 0.09242 -0.0831 0.7843 0.0173
-10.000 -0.0575 0.09223 0.08974 -0.0846 0.7745 0.0175
-9.750 -0.2511 0.02844 0.02502 -0.1524 0.7788 0.0163
-9.500 -0.2054 0.02327 0.01943 -0.1676 0.7692 0.0170
-9.250 -0.1696 0.02247 0.01853 -0.1717 0.7580 0.0173
-9.000 -0.1355 0.02185 0.01781 -0.1748 0.7444 0.0176
-8.750 -0.1028 0.02126 0.01710 -0.1773 0.7279 0.0179
-8.500 -0.0698 0.02046 0.01611 -0.1800 0.7073 0.0185
-8.250 -0.0353 0.01931 0.01465 -0.1831 0.6841 0.0195
-7.500 0.0638 0.01661 0.01135 -0.1898 0.6361 0.0214
-7.250 0.0952 0.01627 0.01093 -0.1911 0.6262 0.0220
-7.000 0.1273 0.01579 0.01033 -0.1924 0.6174 0.0227
-6.750 0.1597 0.01535 0.00976 -0.1937 0.6104 0.0236
-6.500 0.1922 0.01520 0.00946 -0.1950 0.6038 0.0243
-6.250 0.2245 0.01407 0.00822 -0.1965 0.5977 0.0252
-6.000 0.2564 0.01356 0.00769 -0.1977 0.5932 0.0259
-5.750 0.2881 0.01321 0.00732 -0.1987 0.5883 0.0265
-5.500 0.3197 0.01295 0.00699 -0.1997 0.5835 0.0274
-5.250 0.3516 0.01266 0.00665 -0.2007 0.5794 0.0283
-5.000 0.3837 0.01234 0.00630 -0.2017 0.5757 0.0289
-4.750 0.4155 0.01214 0.00603 -0.2026 0.5719 0.0294
-4.500 0.4483 0.01176 0.00560 -0.2038 0.5683 0.0300
-4.250 0.4832 0.01124 0.00504 -0.2058 0.5646 0.0311
-4.000 0.5165 0.01095 0.00474 -0.2071 0.5622 0.0319
-3.750 0.5495 0.01071 0.00447 -0.2084 0.5595 0.0326
-3.500 0.5821 0.01051 0.00423 -0.2095 0.5567 0.0334
-3.250 0.6144 0.01035 0.00402 -0.2106 0.5540 0.0342
-3.000 0.6460 0.01026 0.00387 -0.2114 0.5512 0.0351
-2.750 0.6770 0.01022 0.00378 -0.2122 0.5482 0.0357
-2.500 0.7099 0.01000 0.00351 -0.2133 0.5464 0.0370
-2.250 0.7417 0.00987 0.00336 -0.2142 0.5442 0.0385
-2.000 0.7729 0.00979 0.00326 -0.2150 0.5420 0.0403
-1.750 0.8037 0.00975 0.00319 -0.2156 0.5394 0.0423
-1.500 0.8342 0.00973 0.00313 -0.2162 0.5356 0.0488
-1.250 0.8742 0.00881 0.00289 -0.2199 0.5309 0.3399
-1.000 0.9047 0.00875 0.00296 -0.2204 0.5275 0.3966
-0.750 0.9341 0.00880 0.00302 -0.2207 0.5245 0.4135
-0.500 0.9633 0.00889 0.00307 -0.2210 0.5218 0.4227
-0.250 0.9922 0.00900 0.00316 -0.2212 0.5188 0.4305
0.000 1.0208 0.00916 0.00326 -0.2213 0.5156 0.4375
0.250 1.0503 0.00918 0.00332 -0.2216 0.5134 0.4432
0.500 1.0795 0.00923 0.00338 -0.2219 0.5107 0.4469
0.750 1.1085 0.00931 0.00344 -0.2221 0.5081 0.4511
1.000 1.1373 0.00940 0.00352 -0.2223 0.5056 0.4563
1.250 1.1660 0.00950 0.00361 -0.2225 0.5031 0.4595
1.500 1.1943 0.00963 0.00372 -0.2227 0.5002 0.4621
1.750 1.2233 0.00969 0.00380 -0.2229 0.4983 0.4643
2.000 1.2523 0.00973 0.00386 -0.2232 0.4960 0.4666
2.250 1.2811 0.00979 0.00393 -0.2234 0.4932 0.4687
2.500 1.3096 0.00988 0.00401 -0.2236 0.4901 0.4707
2.750 1.3378 0.00996 0.00409 -0.2238 0.4870 0.4740
3.000 1.3655 0.01011 0.00423 -0.2239 0.4836 0.4769
3.250 1.3942 0.01015 0.00432 -0.2241 0.4813 0.4796
3.500 1.4227 0.01021 0.00441 -0.2244 0.4783 0.4820
3.750 1.4508 0.01030 0.00451 -0.2245 0.4747 0.4845
4.000 1.4782 0.01044 0.00463 -0.2245 0.4708 0.4869
4.250 1.5057 0.01055 0.00475 -0.2246 0.4669 0.4899
4.500 1.5339 0.01059 0.00485 -0.2248 0.4616 0.4924
4.750 1.5609 0.01073 0.00498 -0.2248 0.4549 0.4948
5.000 1.5880 0.01085 0.00512 -0.2248 0.4480 0.4972
5.250 1.6139 0.01105 0.00527 -0.2246 0.4349 0.4998
5.500 1.6384 0.01134 0.00547 -0.2242 0.4126 0.5023
5.750 1.6594 0.01189 0.00583 -0.2233 0.3804 0.5043
6.000 1.6777 0.01261 0.00637 -0.2219 0.3470 0.5073
6.250 1.6970 0.01324 0.00688 -0.2206 0.3236 0.5098
6.500 1.7161 0.01383 0.00738 -0.2194 0.3052 0.5123
6.750 1.7352 0.01439 0.00787 -0.2181 0.2897 0.5149
7.000 1.7542 0.01491 0.00833 -0.2168 0.2768 0.5175
7.250 1.7723 0.01543 0.00880 -0.2153 0.2657 0.5198
7.500 1.7882 0.01600 0.00932 -0.2135 0.2536 0.5225
7.750 1.8026 0.01653 0.00984 -0.2113 0.2425 0.5256
8.000 1.8130 0.01711 0.01041 -0.2084 0.2333 0.5285
8.250 1.8241 0.01786 0.01111 -0.2059 0.2231 0.5314
8.500 1.8370 0.01855 0.01179 -0.2038 0.2135 0.5343
8.750 1.8472 0.01944 0.01264 -0.2013 0.2022 0.5367
9.000 1.8539 0.02058 0.01372 -0.1986 0.1874 0.5398
9.250 1.8501 0.02245 0.01545 -0.1947 0.1615 0.5423
9.500 1.8243 0.02607 0.01878 -0.1886 0.1151 0.5439
9.750 1.7994 0.03006 0.02262 -0.1834 0.0767 0.5456
10.000 1.7918 0.03291 0.02544 -0.1804 0.0606 0.5479
10.250 1.7892 0.03544 0.02795 -0.1781 0.0489 0.5505
10.500 1.7767 0.03897 0.03139 -0.1752 0.0274 0.5525
10.750 1.7677 0.04237 0.03478 -0.1728 0.0160 0.5548
11.000 1.7704 0.04473 0.03723 -0.1714 0.0149 0.5582
11.250 1.7713 0.04733 0.03992 -0.1700 0.0139 0.5615
11.500 1.7717 0.05009 0.04277 -0.1687 0.0130 0.5648
11.750 1.7742 0.05269 0.04544 -0.1677 0.0126 0.5681
12.000 1.7760 0.05541 0.04825 -0.1667 0.0122 0.5713
12.250 1.7765 0.05832 0.05126 -0.1657 0.0117 0.5749
12.500 1.7760 0.06140 0.05442 -0.1648 0.0114 0.5785
12.750 1.7735 0.06476 0.05787 -0.1639 0.0110 0.5821
13.000 1.7691 0.06838 0.06158 -0.1631 0.0106 0.5853
13.250 1.7612 0.07249 0.06582 -0.1622 0.0102 0.5887
13.500 1.7611 0.07563 0.06905 -0.1616 0.0101 0.5931
13.750 1.7594 0.07901 0.07252 -0.1610 0.0099 0.5978
14.000 1.7567 0.08255 0.07615 -0.1605 0.0097 0.6023
14.250 1.7541 0.08610 0.07979 -0.1601 0.0095 0.6072
14.500 1.7500 0.08986 0.08364 -0.1597 0.0093 0.6124
14.750 1.7451 0.09376 0.08764 -0.1594 0.0091 0.6174
15.000 1.7409 0.09761 0.09159 -0.1592 0.0089 0.6231
15.250 1.7353 0.10172 0.09580 -0.1591 0.0087 0.6292
15.500 1.7289 0.10597 0.10015 -0.1591 0.0086 0.6355
15.750 1.7220 0.11028 0.10456 -0.1592 0.0084 0.6427
16.000 1.7112 0.11527 0.10967 -0.1596 0.0082 0.6497
|
Polar data table (+)
Polar graphs
<< Back to GOE 242 (MVA PR.2) AIRFOIL (goe242-il)