GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 391 AIRFOIL (goe391-il) Reynolds number: 100,000 Max Cl/Cd: 58.35 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe391-il-100000-n5.txt Download as CSV file: xf-goe391-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 391 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4075 0.09516 0.09027 -0.0229 1.0000 0.0267
-7.500 -0.4102 0.09287 0.08805 -0.0223 1.0000 0.0268
-7.250 -0.4133 0.09038 0.08564 -0.0218 1.0000 0.0274
-7.000 -0.4132 0.08769 0.08302 -0.0221 1.0000 0.0277
-6.750 -0.4123 0.08498 0.08035 -0.0226 1.0000 0.0280
-6.500 -0.4104 0.08220 0.07761 -0.0232 1.0000 0.0284
-6.250 -0.4070 0.07939 0.07483 -0.0239 1.0000 0.0287
-6.000 -0.4023 0.07641 0.07186 -0.0248 1.0000 0.0292
-5.750 -0.3958 0.07334 0.06879 -0.0258 1.0000 0.0296
-5.500 -0.3866 0.07020 0.06564 -0.0273 1.0000 0.0312
-5.250 -0.3664 0.06732 0.06262 -0.0317 1.0000 0.0337
-5.000 -0.3461 0.06438 0.05951 -0.0345 1.0000 0.0342
-4.750 -0.3276 0.06128 0.05621 -0.0360 1.0000 0.0344
-4.500 -0.3145 0.05714 0.05201 -0.0363 1.0000 0.0348
-4.250 -0.3065 0.05306 0.04794 -0.0356 1.0000 0.0356
-4.000 -0.2926 0.04975 0.04457 -0.0354 1.0000 0.0367
-3.750 -0.2734 0.04659 0.04125 -0.0359 1.0000 0.0373
-3.500 -0.2445 0.04257 0.03697 -0.0377 0.9984 0.0295
-3.250 -0.1971 0.03752 0.03123 -0.0410 0.9952 0.0244
-3.000 -0.1693 0.03464 0.02824 -0.0435 0.9912 0.0270
-2.750 -0.1334 0.03186 0.02508 -0.0456 0.9878 0.0301
-2.500 -0.0989 0.02884 0.02156 -0.0469 0.9841 0.0298
-2.250 -0.0638 0.02611 0.01827 -0.0479 0.9808 0.0306
-2.000 -0.0270 0.02404 0.01550 -0.0489 0.9780 0.0351
-1.750 0.0033 0.02221 0.01341 -0.0496 0.9738 0.0378
-1.500 0.0370 0.02108 0.01189 -0.0504 0.9700 0.0439
-1.250 0.0717 0.01965 0.01018 -0.0517 0.9673 0.0482
-1.000 0.1007 0.01892 0.00933 -0.0520 0.9619 0.0540
-0.750 0.1339 0.01829 0.00852 -0.0530 0.9576 0.0579
-0.500 0.1671 0.01763 0.00778 -0.0541 0.9537 0.0585
-0.250 0.1951 0.01710 0.00721 -0.0542 0.9475 0.0597
0.000 0.2294 0.01671 0.00676 -0.0555 0.9430 0.0624
0.250 0.2602 0.01648 0.00645 -0.0562 0.9367 0.0679
0.500 0.2957 0.01621 0.00614 -0.0577 0.9303 0.0827
0.750 0.3499 0.01392 0.00607 -0.0634 0.9293 1.0000
1.000 0.3823 0.01391 0.00593 -0.0642 0.9197 1.0000
1.250 0.4212 0.01385 0.00578 -0.0664 0.9126 1.0000
1.500 0.4542 0.01379 0.00569 -0.0672 0.9027 1.0000
1.750 0.4864 0.01374 0.00564 -0.0679 0.8923 1.0000
2.000 0.5204 0.01360 0.00552 -0.0688 0.8805 1.0000
2.250 0.5531 0.01346 0.00542 -0.0694 0.8675 1.0000
2.500 0.5842 0.01334 0.00535 -0.0696 0.8530 1.0000
2.750 0.6150 0.01322 0.00534 -0.0697 0.8366 1.0000
3.000 0.6468 0.01310 0.00530 -0.0700 0.8191 1.0000
3.250 0.6763 0.01296 0.00525 -0.0696 0.7917 1.0000
3.500 0.7060 0.01279 0.00511 -0.0690 0.7442 1.0000
3.750 0.7373 0.01276 0.00496 -0.0687 0.6793 1.0000
4.000 0.7644 0.01310 0.00493 -0.0677 0.5910 1.0000
4.250 0.7815 0.01394 0.00516 -0.0652 0.4637 1.0000
4.500 0.7958 0.01504 0.00563 -0.0627 0.3428 1.0000
4.750 0.8136 0.01599 0.00623 -0.0610 0.2600 1.0000
5.000 0.8303 0.01716 0.00691 -0.0593 0.1624 1.0000
5.250 0.8477 0.01839 0.00777 -0.0577 0.0901 1.0000
5.500 0.8666 0.01946 0.00877 -0.0561 0.0715 1.0000
5.750 0.8864 0.02038 0.00990 -0.0546 0.0649 1.0000
6.000 0.9052 0.02142 0.01107 -0.0530 0.0576 1.0000
6.250 0.9242 0.02243 0.01221 -0.0515 0.0485 1.0000
6.500 0.9408 0.02390 0.01378 -0.0497 0.0410 1.0000
6.750 0.9564 0.02580 0.01564 -0.0480 0.0337 1.0000
7.000 0.9774 0.02736 0.01751 -0.0465 0.0283 1.0000
7.250 0.9961 0.02950 0.01976 -0.0453 0.0241 1.0000
7.500 1.0183 0.03212 0.02272 -0.0441 0.0221 1.0000
7.750 1.0387 0.03448 0.02557 -0.0425 0.0192 1.0000
8.000 1.0559 0.03724 0.02878 -0.0407 0.0175 1.0000
8.250 1.0692 0.04051 0.03253 -0.0385 0.0166 1.0000
8.500 1.0784 0.04396 0.03647 -0.0360 0.0161 1.0000
8.750 1.0832 0.04763 0.04060 -0.0332 0.0157 1.0000
9.000 1.0842 0.05129 0.04469 -0.0304 0.0155 1.0000
9.250 1.0824 0.05462 0.04835 -0.0276 0.0149 1.0000
9.500 1.0760 0.05820 0.05226 -0.0248 0.0148 1.0000
9.750 1.0669 0.06112 0.05538 -0.0219 0.0143 1.0000
10.000 1.0531 0.06415 0.05857 -0.0191 0.0138 1.0000
10.250 1.0332 0.06859 0.06332 -0.0168 0.0144 1.0000
10.500 1.0151 0.07280 0.06771 -0.0163 0.0144 1.0000
10.750 0.9833 0.08069 0.07588 -0.0188 0.0155 1.0000
11.000 0.9574 0.08943 0.08475 -0.0243 0.0164 1.0000
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Polar data table (+)
Polar graphs
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