GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 593 AIRFOIL (goe593-il) Reynolds number: 200,000 Max Cl/Cd: 69.9 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe593-il-200000-n5.txt Download as CSV file: xf-goe593-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 593 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3975 0.09044 0.08695 -0.0419 1.0000 0.0237
-9.500 -0.4052 0.08192 0.07847 -0.0492 0.9962 0.0244
-9.000 -0.5328 0.03391 0.02873 -0.0856 0.9573 0.0253
-8.750 -0.5085 0.03240 0.02713 -0.0866 0.9531 0.0260
-8.500 -0.4839 0.03128 0.02590 -0.0872 0.9486 0.0268
-8.250 -0.4636 0.02967 0.02405 -0.0870 0.9423 0.0280
-8.000 -0.4396 0.02728 0.02116 -0.0878 0.9385 0.0296
-7.750 -0.4195 0.02525 0.01865 -0.0872 0.9326 0.0308
-7.500 -0.3937 0.02420 0.01755 -0.0874 0.9277 0.0319
-7.250 -0.3630 0.02331 0.01655 -0.0885 0.9246 0.0333
-7.000 -0.3302 0.02219 0.01517 -0.0899 0.9222 0.0352
-6.750 -0.3079 0.02120 0.01392 -0.0889 0.9150 0.0364
-6.500 -0.2773 0.02011 0.01267 -0.0898 0.9109 0.0380
-6.250 -0.2434 0.01931 0.01183 -0.0913 0.9079 0.0396
-6.000 -0.2140 0.01857 0.01099 -0.0917 0.9029 0.0410
-5.750 -0.1861 0.01790 0.01019 -0.0917 0.8967 0.0427
-5.500 -0.1525 0.01724 0.00937 -0.0928 0.8926 0.0445
-5.250 -0.1220 0.01645 0.00854 -0.0935 0.8875 0.0462
-5.000 -0.0959 0.01592 0.00798 -0.0932 0.8801 0.0477
-4.750 -0.0627 0.01538 0.00739 -0.0943 0.8753 0.0499
-4.500 -0.0364 0.01500 0.00694 -0.0939 0.8676 0.0524
-4.250 -0.0072 0.01454 0.00642 -0.0941 0.8610 0.0549
-4.000 0.0214 0.01410 0.00598 -0.0942 0.8542 0.0580
-3.750 0.0480 0.01378 0.00561 -0.0939 0.8459 0.0619
-3.500 0.0772 0.01344 0.00526 -0.0941 0.8390 0.0682
-3.250 0.1028 0.01316 0.00500 -0.0935 0.8300 0.0787
-3.000 0.1309 0.01289 0.00477 -0.0935 0.8221 0.0955
-2.750 0.1577 0.01269 0.00456 -0.0931 0.8128 0.1132
-2.500 0.1841 0.01250 0.00437 -0.0927 0.8030 0.1296
-2.250 0.2125 0.01230 0.00415 -0.0927 0.7932 0.1478
-2.000 0.2375 0.01212 0.00398 -0.0919 0.7808 0.1669
-1.750 0.2624 0.01190 0.00383 -0.0913 0.7686 0.1962
-1.500 0.2868 0.01159 0.00372 -0.0905 0.7571 0.2591
-1.250 0.3104 0.01120 0.00359 -0.0897 0.7468 0.3480
-1.000 0.3288 0.01068 0.00357 -0.0878 0.7358 0.5002
-0.750 0.3481 0.01026 0.00356 -0.0858 0.7259 0.6331
-0.500 0.3727 0.00993 0.00361 -0.0845 0.7157 0.7672
-0.250 0.4296 0.00988 0.00372 -0.0900 0.7040 0.8918
0.000 0.4836 0.00997 0.00372 -0.0952 0.6918 0.9407
0.250 0.5273 0.01008 0.00371 -0.0984 0.6793 0.9639
0.500 0.5720 0.01022 0.00371 -0.1018 0.6667 0.9851
0.750 0.6233 0.01031 0.00369 -0.1069 0.6527 1.0000
1.000 0.6435 0.01040 0.00370 -0.1053 0.6406 1.0000
1.250 0.6637 0.01050 0.00371 -0.1037 0.6280 1.0000
1.500 0.6840 0.01061 0.00374 -0.1021 0.6154 1.0000
1.750 0.7042 0.01074 0.00378 -0.1005 0.6023 1.0000
2.000 0.7241 0.01087 0.00384 -0.0988 0.5882 1.0000
2.250 0.7438 0.01101 0.00390 -0.0971 0.5732 1.0000
2.500 0.7631 0.01117 0.00398 -0.0953 0.5568 1.0000
2.750 0.7820 0.01135 0.00407 -0.0934 0.5392 1.0000
3.000 0.8008 0.01154 0.00417 -0.0916 0.5210 1.0000
3.250 0.8193 0.01174 0.00429 -0.0896 0.5023 1.0000
3.500 0.8374 0.01198 0.00444 -0.0876 0.4831 1.0000
3.750 0.8548 0.01224 0.00459 -0.0855 0.4641 1.0000
4.000 0.8719 0.01252 0.00477 -0.0833 0.4457 1.0000
4.250 0.8889 0.01282 0.00498 -0.0812 0.4282 1.0000
4.500 0.9063 0.01313 0.00520 -0.0792 0.4124 1.0000
4.750 0.9242 0.01343 0.00543 -0.0772 0.3983 1.0000
5.000 0.9426 0.01372 0.00569 -0.0754 0.3858 1.0000
5.250 0.9610 0.01403 0.00596 -0.0736 0.3743 1.0000
5.500 0.9788 0.01436 0.00624 -0.0718 0.3639 1.0000
5.750 0.9973 0.01467 0.00653 -0.0701 0.3534 1.0000
6.000 1.0158 0.01500 0.00684 -0.0683 0.3443 1.0000
6.250 1.0336 0.01535 0.00716 -0.0665 0.3354 1.0000
6.500 1.0516 0.01567 0.00749 -0.0648 0.3260 1.0000
6.750 1.0673 0.01605 0.00783 -0.0626 0.3172 1.0000
7.000 1.0841 0.01637 0.00817 -0.0606 0.3073 1.0000
7.250 1.1004 0.01674 0.00853 -0.0586 0.2995 1.0000
7.500 1.1172 0.01710 0.00891 -0.0567 0.2911 1.0000
7.750 1.1336 0.01749 0.00931 -0.0548 0.2835 1.0000
8.000 1.1504 0.01786 0.00972 -0.0530 0.2757 1.0000
8.250 1.1664 0.01828 0.01015 -0.0511 0.2683 1.0000
8.500 1.1824 0.01869 0.01059 -0.0492 0.2595 1.0000
8.750 1.1978 0.01913 0.01107 -0.0473 0.2508 1.0000
9.000 1.2127 0.01960 0.01157 -0.0454 0.2424 1.0000
9.250 1.2287 0.02006 0.01209 -0.0437 0.2350 1.0000
9.500 1.2433 0.02058 0.01264 -0.0418 0.2272 1.0000
9.750 1.2585 0.02109 0.01323 -0.0401 0.2195 1.0000
10.000 1.2713 0.02171 0.01388 -0.0381 0.2105 1.0000
10.250 1.2852 0.02230 0.01454 -0.0363 0.1997 1.0000
10.500 1.2970 0.02302 0.01529 -0.0344 0.1867 1.0000
10.750 1.3069 0.02386 0.01613 -0.0323 0.1704 1.0000
11.000 1.3137 0.02491 0.01714 -0.0300 0.1494 1.0000
11.250 1.3156 0.02634 0.01846 -0.0274 0.1253 1.0000
11.500 1.3167 0.02794 0.01995 -0.0249 0.1064 1.0000
11.750 1.3177 0.02963 0.02159 -0.0226 0.0930 1.0000
12.000 1.3198 0.03130 0.02326 -0.0205 0.0841 1.0000
12.250 1.3208 0.03312 0.02509 -0.0187 0.0776 1.0000
12.500 1.3248 0.03478 0.02682 -0.0171 0.0723 1.0000
12.750 1.3258 0.03675 0.02883 -0.0156 0.0680 1.0000
13.000 1.3272 0.03877 0.03094 -0.0143 0.0652 1.0000
13.250 1.3310 0.04064 0.03294 -0.0133 0.0624 1.0000
13.500 1.3323 0.04283 0.03521 -0.0123 0.0594 1.0000
13.750 1.3307 0.04537 0.03782 -0.0115 0.0569 1.0000
14.000 1.3285 0.04809 0.04062 -0.0109 0.0549 1.0000
14.250 1.3313 0.05037 0.04305 -0.0104 0.0525 1.0000
14.500 1.3314 0.05304 0.04584 -0.0102 0.0502 1.0000
14.750 1.3289 0.05609 0.04897 -0.0101 0.0479 1.0000
15.000 1.3229 0.05965 0.05263 -0.0102 0.0462 1.0000
15.250 1.3223 0.06268 0.05580 -0.0104 0.0442 1.0000
15.500 1.3207 0.06592 0.05918 -0.0108 0.0421 1.0000
15.750 1.3166 0.06959 0.06295 -0.0114 0.0402 1.0000
16.000 1.3093 0.07380 0.06723 -0.0124 0.0383 1.0000
16.250 1.3058 0.07759 0.07116 -0.0132 0.0362 1.0000
16.500 1.3012 0.08164 0.07533 -0.0143 0.0340 1.0000
16.750 1.2939 0.08616 0.07995 -0.0157 0.0326 1.0000
17.000 1.2853 0.09097 0.08484 -0.0173 0.0312 1.0000
17.250 1.2796 0.09538 0.08939 -0.0187 0.0295 1.0000
17.500 1.2729 0.10003 0.09416 -0.0204 0.0279 1.0000
17.750 1.2641 0.10513 0.09933 -0.0224 0.0266 1.0000
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