GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 574 AIRFOIL (goe574-il) Reynolds number: 200,000 Max Cl/Cd: 74.46 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe574-il-200000.txt Download as CSV file: xf-goe574-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 574 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3607 0.09956 0.09657 -0.0318 1.0000 0.0299
-7.500 -0.3677 0.09718 0.09425 -0.0314 1.0000 0.0299
-7.250 -0.3761 0.09494 0.09208 -0.0305 1.0000 0.0299
-7.000 -0.3705 0.08798 0.08516 -0.0313 0.9974 0.0308
-6.750 -0.3490 0.08378 0.08095 -0.0332 0.9937 0.0319
-6.500 -0.3228 0.07949 0.07663 -0.0384 0.9876 0.0341
-6.250 -0.2941 0.07433 0.07139 -0.0465 0.9793 0.0366
-6.000 -0.2574 0.06835 0.06527 -0.0583 0.9687 0.0398
-5.750 -0.2187 0.06321 0.05980 -0.0678 0.9569 0.0409
-5.500 -0.2048 0.05635 0.05298 -0.0703 0.9506 0.0424
-5.250 -0.1856 0.05333 0.04996 -0.0710 0.9397 0.0443
-5.000 -0.1614 0.04984 0.04635 -0.0733 0.9286 0.0477
-4.750 -0.0850 0.02795 0.02444 -0.0807 0.8994 0.0589
-4.500 -0.0583 0.02372 0.01972 -0.0836 0.8893 0.0684
-4.250 -0.0258 0.02070 0.01670 -0.0862 0.8818 0.0738
-4.000 -0.0489 0.03525 0.03089 -0.0818 0.8901 0.0734
-3.750 -0.0133 0.03195 0.02726 -0.0844 0.8818 0.0850
-3.500 0.0247 0.02924 0.02427 -0.0873 0.8714 0.0993
-3.250 0.0677 0.02715 0.02194 -0.0912 0.8591 0.1188
-3.000 -0.0657 0.08234 0.07933 -0.0923 0.9170 0.0903
-2.750 0.1655 0.01848 0.01137 -0.0962 0.8336 0.0645
-2.500 0.2105 0.01651 0.00894 -0.0994 0.8167 0.0619
-2.250 0.2507 0.01537 0.00745 -0.1017 0.7986 0.0616
-2.000 0.2812 0.01486 0.00671 -0.1020 0.7788 0.0646
-1.750 0.3093 0.01426 0.00594 -0.1017 0.7593 0.0650
-1.500 0.3358 0.01382 0.00534 -0.1012 0.7404 0.0658
-1.250 0.3580 0.01344 0.00487 -0.0998 0.7209 0.0672
-1.000 0.3792 0.01305 0.00439 -0.0982 0.7020 0.0701
-0.750 0.4015 0.01290 0.00413 -0.0969 0.6842 0.0757
-0.500 0.5760 0.01076 0.00419 -0.1295 0.6566 1.0000
-0.250 0.5978 0.01092 0.00412 -0.1282 0.6407 1.0000
0.000 0.6199 0.01109 0.00409 -0.1270 0.6264 1.0000
0.250 0.6422 0.01126 0.00408 -0.1258 0.6134 1.0000
0.500 0.6647 0.01143 0.00411 -0.1248 0.6018 1.0000
0.750 0.6879 0.01161 0.00414 -0.1239 0.5918 1.0000
1.000 0.7114 0.01179 0.00419 -0.1231 0.5830 1.0000
1.250 0.7346 0.01197 0.00430 -0.1222 0.5747 1.0000
1.500 0.7592 0.01217 0.00438 -0.1216 0.5680 1.0000
1.750 0.7826 0.01235 0.00453 -0.1208 0.5613 1.0000
2.000 0.8068 0.01255 0.00465 -0.1201 0.5553 1.0000
2.250 0.8311 0.01276 0.00484 -0.1196 0.5498 1.0000
2.500 0.8545 0.01295 0.00502 -0.1187 0.5441 1.0000
2.750 0.8797 0.01318 0.00520 -0.1183 0.5397 1.0000
3.000 0.9039 0.01342 0.00544 -0.1177 0.5355 1.0000
3.250 0.9274 0.01364 0.00572 -0.1170 0.5310 1.0000
3.500 0.9521 0.01388 0.00595 -0.1165 0.5268 1.0000
3.750 0.9781 0.01417 0.00622 -0.1163 0.5232 1.0000
4.000 0.9990 0.01438 0.00653 -0.1150 0.5182 1.0000
4.250 1.0223 0.01460 0.00679 -0.1141 0.5130 1.0000
4.500 1.0436 0.01481 0.00702 -0.1128 0.5061 1.0000
4.750 1.0588 0.01483 0.00701 -0.1101 0.4923 1.0000
5.000 1.0764 0.01493 0.00706 -0.1079 0.4805 1.0000
5.250 1.0925 0.01503 0.00728 -0.1055 0.4715 1.0000
5.500 1.1066 0.01510 0.00739 -0.1025 0.4584 1.0000
5.750 1.1177 0.01514 0.00744 -0.0989 0.4424 1.0000
6.000 1.1292 0.01521 0.00754 -0.0954 0.4267 1.0000
6.250 1.1362 0.01526 0.00761 -0.0910 0.4038 1.0000
6.500 1.1381 0.01537 0.00766 -0.0854 0.3656 1.0000
6.750 1.1266 0.01621 0.00793 -0.0776 0.2554 1.0000
7.000 1.1069 0.01806 0.00909 -0.0690 0.1529 1.0000
7.250 1.0841 0.02007 0.01051 -0.0602 0.0479 1.0000
7.500 1.0877 0.02098 0.01144 -0.0558 0.0379 1.0000
7.750 1.0959 0.02172 0.01233 -0.0523 0.0349 1.0000
8.000 1.1019 0.02259 0.01335 -0.0486 0.0326 1.0000
8.250 1.1057 0.02360 0.01450 -0.0448 0.0311 1.0000
8.500 1.1045 0.02490 0.01595 -0.0405 0.0297 1.0000
8.750 1.1006 0.02641 0.01760 -0.0361 0.0289 1.0000
9.000 1.0909 0.02840 0.01970 -0.0316 0.0281 1.0000
9.250 1.0940 0.02978 0.02119 -0.0289 0.0269 1.0000
9.500 1.0916 0.03168 0.02319 -0.0261 0.0268 1.0000
9.750 1.0900 0.03371 0.02531 -0.0235 0.0265 1.0000
10.000 1.0899 0.03579 0.02750 -0.0213 0.0262 1.0000
10.250 1.0925 0.03775 0.02953 -0.0192 0.0260 1.0000
10.500 1.0999 0.03946 0.03127 -0.0171 0.0259 1.0000
10.750 1.1148 0.04087 0.03271 -0.0151 0.0260 1.0000
11.000 1.1430 0.04206 0.03393 -0.0135 0.0263 1.0000
11.250 1.1686 0.04352 0.03550 -0.0125 0.0254 1.0000
17.500 0.7069 0.17201 0.16878 -0.0402 0.0666 1.0000
17.750 0.7141 0.17402 0.17082 -0.0406 0.0635 1.0000
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Polar data table (+)
Polar graphs
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