GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 411 AIRFOIL (goe411-il) Reynolds number: 500,000 Max Cl/Cd: 45.8 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe411-il-500000.txt Download as CSV file: xf-goe411-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 411 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6534 0.09980 0.09741 -0.0348 1.0000 0.0149
-13.250 -0.6913 0.08727 0.08470 -0.0432 1.0000 0.0140
-13.000 -0.7207 0.07869 0.07596 -0.0488 1.0000 0.0138
-12.750 -0.7470 0.07203 0.06912 -0.0528 1.0000 0.0136
-12.500 -0.7609 0.06756 0.06458 -0.0545 1.0000 0.0138
-12.250 -0.7772 0.06333 0.06025 -0.0556 1.0000 0.0139
-12.000 -0.7960 0.05945 0.05622 -0.0559 1.0000 0.0139
-11.750 -0.8186 0.05597 0.05255 -0.0548 1.0000 0.0137
-11.500 -0.8341 0.05320 0.04965 -0.0528 1.0000 0.0137
-11.250 -0.8431 0.05095 0.04734 -0.0505 1.0000 0.0142
-11.000 -0.8578 0.04884 0.04509 -0.0469 1.0000 0.0143
-10.750 -0.8720 0.04704 0.04319 -0.0425 1.0000 0.0146
-10.500 -0.8878 0.04552 0.04153 -0.0369 1.0000 0.0146
-10.250 -0.9039 0.04417 0.04007 -0.0306 1.0000 0.0148
-10.000 -0.9123 0.04260 0.03837 -0.0256 1.0000 0.0152
-9.750 -0.9192 0.04087 0.03648 -0.0206 1.0000 0.0153
-9.500 -0.9229 0.03962 0.03508 -0.0159 1.0000 0.0161
-9.250 -0.9237 0.03847 0.03376 -0.0114 1.0000 0.0167
-7.000 -0.8007 0.02138 0.01500 0.0091 0.9951 0.0143
-6.750 -0.7702 0.01986 0.01339 0.0084 0.9930 0.0142
-6.500 -0.7412 0.01867 0.01215 0.0077 0.9895 0.0145
-6.250 -0.7104 0.01757 0.01100 0.0066 0.9862 0.0151
-6.000 -0.6782 0.01668 0.01006 0.0052 0.9838 0.0160
-5.750 -0.6512 0.01596 0.00929 0.0050 0.9798 0.0171
-5.500 -0.6246 0.01517 0.00841 0.0050 0.9754 0.0176
-5.250 -0.5923 0.01452 0.00770 0.0038 0.9725 0.0182
-5.000 -0.5601 0.01370 0.00675 0.0025 0.9704 0.0196
-4.750 -0.5357 0.01310 0.00605 0.0031 0.9649 0.0221
-4.500 -0.5045 0.01268 0.00553 0.0023 0.9611 0.0252
-4.250 -0.4698 0.01223 0.00506 0.0007 0.9586 0.0356
-4.000 -0.4475 0.01043 0.00425 0.0007 0.9560 0.2394
-3.750 -0.4335 0.00951 0.00390 0.0031 0.9477 0.3571
-3.500 -0.4021 0.00897 0.00365 0.0020 0.9448 0.4276
-3.250 -0.3661 0.00861 0.00343 0.0001 0.9429 0.4730
-3.000 -0.3418 0.00833 0.00327 0.0008 0.9364 0.5107
-2.750 -0.3088 0.00807 0.00308 -0.0004 0.9321 0.5370
-2.500 -0.2727 0.00781 0.00289 -0.0022 0.9289 0.5623
-2.250 -0.2469 0.00763 0.00274 -0.0018 0.9208 0.5774
-2.000 -0.2129 0.00740 0.00254 -0.0031 0.9153 0.5963
-1.750 -0.1861 0.00722 0.00241 -0.0028 0.9059 0.6149
-1.500 -0.1542 0.00700 0.00225 -0.0037 0.8979 0.6337
-1.250 -0.1259 0.00682 0.00212 -0.0037 0.8870 0.6549
-1.000 -0.0999 0.00664 0.00204 -0.0033 0.8743 0.6804
-0.750 -0.0740 0.00649 0.00197 -0.0027 0.8603 0.7112
-0.250 -0.0247 0.00632 0.00191 -0.0009 0.8237 0.7761
0.000 0.0000 0.00631 0.00190 0.0000 0.8017 0.8015
0.250 0.0247 0.00632 0.00191 0.0009 0.7762 0.8237
0.750 0.0740 0.00649 0.00197 0.0027 0.7111 0.8603
1.000 0.0998 0.00665 0.00203 0.0033 0.6796 0.8743
1.250 0.1258 0.00682 0.00212 0.0038 0.6544 0.8870
1.500 0.1543 0.00700 0.00225 0.0037 0.6336 0.8978
1.750 0.1860 0.00722 0.00241 0.0029 0.6142 0.9059
2.000 0.2128 0.00739 0.00254 0.0031 0.5969 0.9153
2.250 0.2469 0.00763 0.00274 0.0018 0.5777 0.9207
2.500 0.2727 0.00781 0.00289 0.0023 0.5617 0.9289
2.750 0.3089 0.00807 0.00309 0.0004 0.5371 0.9321
3.000 0.3419 0.00833 0.00327 -0.0008 0.5097 0.9364
3.250 0.3663 0.00862 0.00343 -0.0001 0.4720 0.9429
3.500 0.4023 0.00897 0.00365 -0.0020 0.4295 0.9448
3.750 0.4342 0.00948 0.00390 -0.0032 0.3626 0.9476
4.000 0.4479 0.01037 0.00425 -0.0007 0.2471 0.9560
4.250 0.4702 0.01222 0.00505 -0.0008 0.0365 0.9586
4.500 0.5045 0.01267 0.00552 -0.0023 0.0254 0.9611
4.750 0.5354 0.01313 0.00608 -0.0031 0.0218 0.9649
5.000 0.5595 0.01375 0.00681 -0.0024 0.0192 0.9704
5.250 0.5925 0.01453 0.00770 -0.0038 0.0183 0.9725
5.500 0.6244 0.01517 0.00842 -0.0049 0.0174 0.9754
5.750 0.6512 0.01598 0.00931 -0.0050 0.0169 0.9798
6.000 0.6777 0.01676 0.01014 -0.0051 0.0159 0.9838
6.250 0.7104 0.01758 0.01101 -0.0066 0.0150 0.9862
6.500 0.7412 0.01864 0.01212 -0.0078 0.0143 0.9895
6.750 0.7699 0.01984 0.01336 -0.0084 0.0139 0.9929
7.000 0.8006 0.02142 0.01506 -0.0090 0.0146 0.9951
10.250 0.9031 0.04424 0.04015 0.0307 0.0148 1.0000
10.500 0.8876 0.04558 0.04160 0.0369 0.0148 1.0000
10.750 0.8768 0.04688 0.04296 0.0417 0.0140 1.0000
11.000 0.8576 0.04885 0.04512 0.0470 0.0145 1.0000
11.250 0.8432 0.05097 0.04736 0.0505 0.0142 1.0000
11.500 0.8339 0.05317 0.04963 0.0528 0.0138 1.0000
11.750 0.8183 0.05594 0.05252 0.0548 0.0137 1.0000
12.000 0.8056 0.05901 0.05569 0.0557 0.0135 1.0000
12.250 0.7783 0.06333 0.06023 0.0556 0.0138 1.0000
12.500 0.7555 0.06829 0.06536 0.0540 0.0140 1.0000
12.750 0.7364 0.07354 0.07074 0.0514 0.0140 1.0000
13.000 0.7224 0.07857 0.07583 0.0488 0.0137 1.0000
13.250 0.6912 0.08754 0.08499 0.0428 0.0141 1.0000
13.500 0.6547 0.09975 0.09736 0.0346 0.0147 1.0000
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