GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 342 AIRFOIL (goe342-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.66 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe342-il-1000000-n5.txt Download as CSV file: xf-goe342-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 342 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2690 0.10180 0.10010 -0.0404 0.9617 0.0053
-9.000 -0.2616 0.09854 0.09681 -0.0419 0.9460 0.0055
-8.750 -0.2529 0.09624 0.09447 -0.0428 0.9299 0.0056
-8.500 -0.2435 0.09411 0.09229 -0.0437 0.9140 0.0057
-8.250 -0.2344 0.09172 0.08985 -0.0449 0.8984 0.0059
-8.000 -0.2256 0.08905 0.08712 -0.0463 0.8827 0.0062
-7.750 -0.2169 0.08609 0.08410 -0.0480 0.8669 0.0063
-7.500 -0.2070 0.08291 0.08086 -0.0505 0.8519 0.0066
-7.250 -0.1937 0.07857 0.07645 -0.0550 0.8380 0.0071
-7.000 -0.1772 0.07424 0.07207 -0.0602 0.8256 0.0075
-6.750 -0.1581 0.07175 0.06951 -0.0636 0.8132 0.0077
-6.500 -0.1376 0.06933 0.06704 -0.0670 0.8014 0.0080
-6.250 -0.1155 0.06654 0.06420 -0.0711 0.7916 0.0084
-5.750 -0.0592 0.05706 0.05459 -0.0858 0.7768 0.0100
-5.500 -0.0323 0.05473 0.05220 -0.0897 0.7703 0.0102
-5.250 -0.0040 0.05228 0.04969 -0.0939 0.7641 0.0106
-5.000 0.0277 0.04913 0.04647 -0.0993 0.7577 0.0116
-4.500 0.1015 0.04128 0.03843 -0.1125 0.7487 0.0131
-4.250 0.1331 0.03920 0.03628 -0.1159 0.7438 0.0136
-4.000 0.1685 0.03639 0.03337 -0.1204 0.7389 0.0147
-3.750 0.2187 0.03040 0.02712 -0.1290 0.7353 0.0161
-3.500 0.2477 0.02924 0.02591 -0.1306 0.7313 0.0164
-3.250 0.2778 0.02793 0.02453 -0.1323 0.7270 0.0169
-3.000 0.3117 0.02583 0.02229 -0.1348 0.7231 0.0176
-2.750 0.3477 0.02326 0.01956 -0.1376 0.7192 0.0183
-2.250 0.4245 0.01638 0.01203 -0.1430 0.7097 0.0204
-2.000 0.4540 0.01555 0.01108 -0.1437 0.7027 0.0206
-1.750 0.4838 0.01461 0.00999 -0.1444 0.6940 0.0209
-1.500 0.5143 0.01353 0.00874 -0.1451 0.6867 0.0212
-1.250 0.5450 0.01243 0.00743 -0.1458 0.6799 0.0213
-1.000 0.5745 0.01178 0.00664 -0.1462 0.6733 0.0217
-0.750 0.6047 0.01090 0.00558 -0.1467 0.6658 0.0218
-0.500 0.6342 0.01021 0.00471 -0.1470 0.6568 0.0219
-0.250 0.6630 0.00973 0.00408 -0.1472 0.6411 0.0224
0.000 0.6907 0.00948 0.00361 -0.1471 0.6042 0.0229
0.250 0.7162 0.00962 0.00336 -0.1468 0.5303 0.0235
0.500 0.7422 0.00977 0.00323 -0.1465 0.4778 0.0239
0.750 0.7687 0.00986 0.00311 -0.1464 0.4347 0.0242
1.000 0.7953 0.00995 0.00302 -0.1462 0.3992 0.0244
1.250 0.8221 0.01001 0.00293 -0.1461 0.3711 0.0246
1.500 0.8489 0.01011 0.00295 -0.1460 0.3516 0.0248
2.000 0.9040 0.01001 0.00275 -0.1460 0.3296 0.0252
2.250 0.9317 0.00992 0.00264 -0.1460 0.3222 0.0254
2.500 0.9595 0.00985 0.00256 -0.1461 0.3154 0.0259
2.750 0.9868 0.00991 0.00257 -0.1460 0.3065 0.0267
3.000 1.0140 0.00997 0.00263 -0.1459 0.2981 0.0277
3.250 1.0411 0.01006 0.00271 -0.1458 0.2917 0.0288
3.500 1.0683 0.01013 0.00278 -0.1457 0.2860 0.0296
3.750 1.0950 0.01026 0.00288 -0.1456 0.2771 0.0304
4.000 1.1218 0.01037 0.00300 -0.1454 0.2690 0.0313
4.250 1.1481 0.01053 0.00313 -0.1452 0.2587 0.0323
4.500 1.1746 0.01067 0.00326 -0.1450 0.2493 0.0327
4.750 1.2006 0.01086 0.00341 -0.1447 0.2359 0.0352
5.000 1.2262 0.01108 0.00362 -0.1444 0.2183 0.0996
5.500 1.2673 0.01135 0.00479 -0.1426 0.1208 1.0000
5.750 1.2916 0.01174 0.00511 -0.1421 0.1075 1.0000
6.000 1.3161 0.01208 0.00541 -0.1416 0.0967 1.0000
6.250 1.3402 0.01246 0.00572 -0.1410 0.0857 1.0000
6.500 1.3639 0.01287 0.00606 -0.1404 0.0722 1.0000
6.750 1.3873 0.01329 0.00642 -0.1398 0.0606 1.0000
7.000 1.4113 0.01364 0.00674 -0.1392 0.0552 1.0000
7.250 1.4347 0.01403 0.00711 -0.1385 0.0488 1.0000
7.500 1.4580 0.01442 0.00749 -0.1379 0.0428 1.0000
7.750 1.4806 0.01487 0.00791 -0.1371 0.0360 1.0000
8.000 1.5002 0.01561 0.00852 -0.1359 0.0197 1.0000
8.250 1.5209 0.01622 0.00911 -0.1348 0.0139 1.0000
8.500 1.5422 0.01672 0.00963 -0.1338 0.0114 1.0000
8.750 1.5633 0.01721 0.01016 -0.1328 0.0101 1.0000
9.000 1.5834 0.01779 0.01076 -0.1317 0.0088 1.0000
9.250 1.6035 0.01831 0.01133 -0.1305 0.0081 1.0000
9.500 1.6233 0.01884 0.01190 -0.1293 0.0075 1.0000
9.750 1.6422 0.01940 0.01251 -0.1280 0.0070 1.0000
10.000 1.6599 0.02004 0.01319 -0.1265 0.0064 1.0000
10.250 1.6754 0.02080 0.01400 -0.1246 0.0058 1.0000
10.500 1.6914 0.02141 0.01467 -0.1228 0.0056 1.0000
10.750 1.7050 0.02204 0.01536 -0.1206 0.0053 1.0000
11.000 1.7173 0.02274 0.01613 -0.1182 0.0050 1.0000
11.250 1.7291 0.02351 0.01698 -0.1159 0.0048 1.0000
11.500 1.7400 0.02437 0.01789 -0.1135 0.0046 1.0000
11.750 1.7501 0.02531 0.01891 -0.1111 0.0044 1.0000
12.000 1.7589 0.02638 0.02005 -0.1087 0.0041 1.0000
12.250 1.7653 0.02769 0.02144 -0.1061 0.0039 1.0000
12.500 1.7722 0.02899 0.02284 -0.1037 0.0038 1.0000
12.750 1.7802 0.03025 0.02418 -0.1017 0.0037 1.0000
13.000 1.7870 0.03164 0.02568 -0.0996 0.0036 1.0000
13.250 1.7930 0.03316 0.02730 -0.0976 0.0035 1.0000
13.500 1.7978 0.03484 0.02907 -0.0956 0.0034 1.0000
13.750 1.8018 0.03663 0.03097 -0.0937 0.0034 1.0000
14.000 1.8049 0.03859 0.03303 -0.0920 0.0033 1.0000
14.250 1.8072 0.04068 0.03523 -0.0904 0.0032 1.0000
14.500 1.8084 0.04295 0.03760 -0.0889 0.0031 1.0000
14.750 1.8092 0.04533 0.04008 -0.0875 0.0030 1.0000
15.000 1.8089 0.04789 0.04275 -0.0863 0.0029 1.0000
15.250 1.8070 0.05070 0.04566 -0.0852 0.0029 1.0000
15.500 1.8044 0.05368 0.04876 -0.0843 0.0028 1.0000
15.750 1.7997 0.05706 0.05225 -0.0836 0.0027 1.0000
16.000 1.7935 0.06076 0.05606 -0.0832 0.0027 1.0000
16.250 1.7850 0.06491 0.06034 -0.0830 0.0026 1.0000
16.500 1.7746 0.06957 0.06513 -0.0832 0.0026 1.0000
16.750 1.7618 0.07487 0.07057 -0.0839 0.0025 1.0000
17.000 1.7466 0.08077 0.07662 -0.0852 0.0025 1.0000
17.250 1.7300 0.08722 0.08323 -0.0869 0.0025 1.0000
17.500 1.7115 0.09427 0.09043 -0.0892 0.0024 1.0000
17.750 1.6927 0.10158 0.09789 -0.0919 0.0024 1.0000
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