GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 711 AIRFOIL (goe711-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.24 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe711-il-1000000.txt Download as CSV file: xf-goe711-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 711 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0705 0.09027 0.08852 -0.0987 0.9588 0.0185
-9.250 -0.0689 0.08656 0.08481 -0.1001 0.9538 0.0186
-9.000 -0.0722 0.08206 0.08032 -0.1013 0.9479 0.0187
-8.750 -0.0669 0.07984 0.07808 -0.1009 0.9426 0.0189
-8.500 -0.0597 0.07763 0.07587 -0.1012 0.9364 0.0190
-8.250 -0.0543 0.07517 0.07341 -0.1019 0.9299 0.0192
-8.000 -0.0499 0.07250 0.07073 -0.1031 0.9233 0.0194
-7.750 -0.0487 0.06963 0.06785 -0.1050 0.9154 0.0197
-7.500 -0.0406 0.06605 0.06424 -0.1091 0.9085 0.0202
-7.250 -0.0327 0.05581 0.05383 -0.1224 0.8989 0.0222
-7.000 -0.0045 0.03527 0.03323 -0.1219 0.8689 0.0226
-6.750 -0.0157 0.04523 0.04297 -0.1278 0.8826 0.0227
-6.500 0.0026 0.04349 0.04117 -0.1284 0.8734 0.0229
-6.250 0.0219 0.04169 0.03928 -0.1291 0.8640 0.0233
-6.000 0.0420 0.03960 0.03706 -0.1299 0.8529 0.0238
-5.750 0.0665 0.03338 0.03032 -0.1311 0.8416 0.0266
-5.500 0.0804 0.02831 0.02496 -0.1316 0.8296 0.0271
-5.250 0.1040 0.02729 0.02383 -0.1319 0.8164 0.0274
-5.000 0.1283 0.02627 0.02269 -0.1321 0.8022 0.0279
-4.750 0.1530 0.02515 0.02141 -0.1322 0.7869 0.0286
-4.500 0.1823 0.02412 0.01990 -0.1315 0.7713 0.0316
-4.250 0.2035 0.01982 0.01519 -0.1317 0.7570 0.0323
-4.000 0.2297 0.01899 0.01426 -0.1319 0.7415 0.0328
-3.750 0.2563 0.01831 0.01345 -0.1321 0.7255 0.0333
-3.500 0.2832 0.01763 0.01262 -0.1322 0.7090 0.0342
-3.250 0.3115 0.01493 0.00923 -0.1315 0.6942 0.0319
-3.000 0.3387 0.01384 0.00802 -0.1315 0.6783 0.0310
-2.750 0.3663 0.01312 0.00711 -0.1315 0.6628 0.0311
-2.500 0.3940 0.01270 0.00653 -0.1315 0.6466 0.0314
-2.250 0.4212 0.01196 0.00562 -0.1315 0.6297 0.0321
-2.000 0.4482 0.01146 0.00503 -0.1315 0.6125 0.0326
-1.750 0.4755 0.01120 0.00469 -0.1315 0.5956 0.0330
-1.500 0.5028 0.01101 0.00442 -0.1315 0.5794 0.0334
-1.250 0.5300 0.01087 0.00420 -0.1315 0.5629 0.0339
-1.000 0.5572 0.01076 0.00400 -0.1315 0.5461 0.0344
-0.750 0.5843 0.01067 0.00383 -0.1315 0.5297 0.0350
-0.500 0.6115 0.01062 0.00370 -0.1316 0.5145 0.0358
-0.250 0.6388 0.01062 0.00362 -0.1316 0.5001 0.0368
0.000 0.6660 0.01064 0.00356 -0.1316 0.4860 0.0374
0.250 0.6929 0.01056 0.00340 -0.1316 0.4718 0.0383
0.750 0.7472 0.01057 0.00328 -0.1317 0.4449 0.0411
1.000 0.7743 0.01062 0.00328 -0.1317 0.4335 0.0429
1.250 0.8012 0.01071 0.00331 -0.1317 0.4225 0.0447
1.500 0.8281 0.01076 0.00331 -0.1317 0.4119 0.0490
1.750 0.8551 0.01083 0.00335 -0.1317 0.4024 0.0538
2.000 0.8788 0.00935 0.00365 -0.1321 0.3931 0.7905
2.250 0.9003 0.00905 0.00373 -0.1304 0.3849 1.0000
2.500 0.9265 0.00924 0.00383 -0.1303 0.3765 1.0000
2.750 0.9531 0.00940 0.00392 -0.1302 0.3693 1.0000
3.000 0.9789 0.00960 0.00405 -0.1301 0.3619 1.0000
3.250 1.0055 0.00975 0.00415 -0.1300 0.3552 1.0000
3.500 1.0306 0.00998 0.00430 -0.1297 0.3472 1.0000
3.750 1.0569 0.01013 0.00442 -0.1297 0.3411 1.0000
4.000 1.0821 0.01034 0.00456 -0.1294 0.3347 1.0000
4.250 1.1074 0.01053 0.00471 -0.1292 0.3285 1.0000
4.500 1.1326 0.01071 0.00486 -0.1290 0.3225 1.0000
4.750 1.1569 0.01094 0.00504 -0.1285 0.3171 1.0000
5.000 1.1820 0.01111 0.00520 -0.1283 0.3134 1.0000
5.250 1.2069 0.01128 0.00536 -0.1280 0.3094 1.0000
5.500 1.2308 0.01150 0.00555 -0.1275 0.3052 1.0000
5.750 1.2535 0.01176 0.00578 -0.1268 0.3005 1.0000
6.000 1.2776 0.01192 0.00595 -0.1264 0.2974 1.0000
6.250 1.2997 0.01212 0.00615 -0.1255 0.2934 1.0000
6.500 1.3203 0.01240 0.00640 -0.1244 0.2886 1.0000
6.750 1.3414 0.01267 0.00665 -0.1234 0.2837 1.0000
7.000 1.3636 0.01290 0.00688 -0.1227 0.2785 1.0000
7.250 1.3835 0.01324 0.00719 -0.1215 0.2716 1.0000
7.500 1.4055 0.01350 0.00745 -0.1208 0.2668 1.0000
7.750 1.4264 0.01381 0.00774 -0.1199 0.2607 1.0000
8.000 1.4462 0.01418 0.00808 -0.1188 0.2546 1.0000
8.250 1.4675 0.01448 0.00839 -0.1180 0.2488 1.0000
8.500 1.4859 0.01493 0.00879 -0.1168 0.2410 1.0000
8.750 1.5053 0.01534 0.00917 -0.1158 0.2318 1.0000
9.000 1.5229 0.01585 0.00964 -0.1144 0.2211 1.0000
9.250 1.5387 0.01645 0.01018 -0.1128 0.2088 1.0000
9.500 1.5517 0.01722 0.01084 -0.1108 0.1918 1.0000
9.750 1.5578 0.01840 0.01184 -0.1078 0.1647 1.0000
10.000 1.5514 0.02033 0.01350 -0.1030 0.1250 1.0000
10.250 1.5513 0.02197 0.01500 -0.0993 0.1013 1.0000
10.500 1.5391 0.02445 0.01727 -0.0942 0.0549 1.0000
10.750 1.5483 0.02562 0.01846 -0.0922 0.0484 1.0000
11.000 1.5596 0.02667 0.01955 -0.0905 0.0429 1.0000
11.250 1.5659 0.02811 0.02096 -0.0884 0.0298 1.0000
11.500 1.5675 0.02992 0.02272 -0.0859 0.0174 1.0000
11.750 1.5747 0.03140 0.02425 -0.0841 0.0156 1.0000
12.000 1.5828 0.03286 0.02577 -0.0826 0.0146 1.0000
12.250 1.5909 0.03437 0.02735 -0.0812 0.0140 1.0000
12.500 1.5971 0.03610 0.02914 -0.0798 0.0134 1.0000
12.750 1.6014 0.03806 0.03118 -0.0783 0.0128 1.0000
13.000 1.6024 0.04043 0.03363 -0.0768 0.0122 1.0000
13.250 1.6043 0.04280 0.03610 -0.0755 0.0119 1.0000
13.500 1.6084 0.04504 0.03841 -0.0746 0.0116 1.0000
13.750 1.6107 0.04753 0.04098 -0.0737 0.0113 1.0000
14.000 1.6110 0.05028 0.04383 -0.0729 0.0111 1.0000
14.250 1.6098 0.05331 0.04695 -0.0722 0.0108 1.0000
14.500 1.6072 0.05660 0.05034 -0.0716 0.0105 1.0000
14.750 1.6030 0.06018 0.05401 -0.0712 0.0103 1.0000
15.000 1.5958 0.06421 0.05814 -0.0709 0.0101 1.0000
15.250 1.5850 0.06879 0.06284 -0.0707 0.0099 1.0000
15.500 1.5701 0.07408 0.06825 -0.0707 0.0097 1.0000
15.750 1.5516 0.08001 0.07433 -0.0710 0.0096 1.0000
16.000 1.5299 0.08650 0.08098 -0.0716 0.0094 1.0000
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