GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 591 AIRFOIL (goe591-il) Reynolds number: 200,000 Max Cl/Cd: 77.18 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe591-il-200000.txt Download as CSV file: xf-goe591-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 591 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2966 0.10340 0.10017 -0.0338 1.0000 0.0485
-8.750 -0.3128 0.10253 0.09940 -0.0310 1.0000 0.0495
-8.500 -0.3195 0.09991 0.09682 -0.0379 0.9959 0.0512
-8.250 -0.3115 0.09480 0.09172 -0.0524 0.9855 0.0517
-8.000 -0.2870 0.08969 0.08661 -0.0473 0.9864 0.0531
-7.750 -0.2614 0.08623 0.08312 -0.0499 0.9836 0.0551
-7.500 -0.2450 0.08259 0.07947 -0.0545 0.9756 0.0574
-7.250 -0.2217 0.07447 0.07118 -0.0813 0.9591 0.0625
-7.000 -0.2051 0.06957 0.06637 -0.0795 0.9574 0.0641
-6.750 -0.1853 0.06717 0.06397 -0.0790 0.9511 0.0659
-6.500 -0.1588 0.06328 0.06002 -0.0842 0.9452 0.0691
-6.250 -0.1331 0.05472 0.05097 -0.1002 0.9335 0.0759
-6.000 -0.1060 0.05145 0.04782 -0.1011 0.9305 0.0777
-5.750 -0.0742 0.04897 0.04532 -0.1035 0.9274 0.0818
-5.500 -0.0549 0.04361 0.03936 -0.1088 0.9157 0.0906
-5.250 -0.0251 0.04046 0.03628 -0.1106 0.9122 0.0926
-5.000 -0.0052 0.03844 0.03420 -0.1103 0.9028 0.0955
-4.750 0.0162 0.02667 0.02071 -0.1116 0.8963 0.0634
-4.500 0.0377 0.02481 0.01860 -0.1104 0.8865 0.0618
-4.250 0.0690 0.02253 0.01590 -0.1111 0.8816 0.0620
-4.000 0.0918 0.02118 0.01422 -0.1099 0.8721 0.0628
-3.750 0.1231 0.01921 0.01194 -0.1104 0.8666 0.0634
-3.500 0.1470 0.01797 0.01055 -0.1095 0.8570 0.0644
-3.250 0.1789 0.01694 0.00939 -0.1099 0.8509 0.0661
-3.000 0.2033 0.01643 0.00882 -0.1090 0.8407 0.0692
-2.750 0.2324 0.01580 0.00805 -0.1088 0.8330 0.0722
-2.500 0.2593 0.01527 0.00740 -0.1082 0.8236 0.0747
-2.250 0.2846 0.01448 0.00663 -0.1075 0.8144 0.0791
-2.000 0.3125 0.01403 0.00613 -0.1072 0.8059 0.0867
-1.750 0.3363 0.01356 0.00571 -0.1062 0.7956 0.1009
-1.500 0.3621 0.01299 0.00527 -0.1055 0.7868 0.1397
-1.250 0.3872 0.01272 0.00511 -0.1048 0.7765 0.1832
-1.000 0.4113 0.01241 0.00497 -0.1040 0.7662 0.2412
-0.750 0.4340 0.01170 0.00485 -0.1031 0.7574 0.4110
-0.500 0.5290 0.01025 0.00472 -0.1161 0.7471 1.0000
-0.250 0.5521 0.01032 0.00463 -0.1150 0.7361 1.0000
0.000 0.5764 0.01038 0.00452 -0.1141 0.7258 1.0000
0.250 0.5992 0.01045 0.00446 -0.1129 0.7141 1.0000
0.500 0.6219 0.01054 0.00444 -0.1117 0.7024 1.0000
0.750 0.6454 0.01064 0.00441 -0.1107 0.6911 1.0000
1.000 0.6697 0.01074 0.00436 -0.1098 0.6803 1.0000
1.250 0.6926 0.01085 0.00437 -0.1086 0.6683 1.0000
1.500 0.7155 0.01098 0.00441 -0.1075 0.6563 1.0000
1.750 0.7388 0.01111 0.00444 -0.1065 0.6446 1.0000
2.000 0.7625 0.01126 0.00447 -0.1055 0.6331 1.0000
2.250 0.7859 0.01140 0.00451 -0.1045 0.6214 1.0000
2.500 0.8084 0.01156 0.00461 -0.1034 0.6093 1.0000
2.750 0.8318 0.01174 0.00473 -0.1024 0.5983 1.0000
3.000 0.8561 0.01194 0.00482 -0.1016 0.5885 1.0000
3.250 0.8792 0.01213 0.00497 -0.1006 0.5779 1.0000
3.500 0.9026 0.01234 0.00514 -0.0997 0.5677 1.0000
3.750 0.9273 0.01257 0.00528 -0.0991 0.5588 1.0000
4.000 0.9501 0.01278 0.00550 -0.0981 0.5488 1.0000
4.250 0.9741 0.01302 0.00570 -0.0973 0.5399 1.0000
4.500 0.9979 0.01325 0.00588 -0.0966 0.5303 1.0000
4.750 1.0204 0.01348 0.00612 -0.0955 0.5200 1.0000
5.000 1.0440 0.01373 0.00632 -0.0947 0.5106 1.0000
5.250 1.0669 0.01396 0.00656 -0.0938 0.5008 1.0000
5.500 1.0893 0.01421 0.00683 -0.0928 0.4907 1.0000
5.750 1.1123 0.01448 0.00705 -0.0919 0.4810 1.0000
6.000 1.1339 0.01471 0.00729 -0.0908 0.4703 1.0000
6.250 1.1554 0.01497 0.00760 -0.0896 0.4598 1.0000
6.500 1.1777 0.01526 0.00787 -0.0886 0.4502 1.0000
6.750 1.1991 0.01554 0.00818 -0.0875 0.4403 1.0000
7.000 1.2203 0.01584 0.00854 -0.0863 0.4305 1.0000
7.250 1.2420 0.01617 0.00885 -0.0853 0.4210 1.0000
7.500 1.2609 0.01645 0.00918 -0.0837 0.4093 1.0000
7.750 1.2788 0.01673 0.00952 -0.0820 0.3967 1.0000
8.000 1.2953 0.01702 0.00985 -0.0800 0.3829 1.0000
8.250 1.3114 0.01734 0.01019 -0.0780 0.3693 1.0000
8.500 1.3262 0.01768 0.01055 -0.0758 0.3552 1.0000
8.750 1.3401 0.01805 0.01094 -0.0735 0.3411 1.0000
9.000 1.3509 0.01845 0.01134 -0.0706 0.3257 1.0000
9.250 1.3604 0.01890 0.01181 -0.0676 0.3107 1.0000
9.500 1.3694 0.01943 0.01235 -0.0646 0.2955 1.0000
9.750 1.3786 0.02004 0.01296 -0.0618 0.2809 1.0000
10.000 1.3869 0.02073 0.01365 -0.0590 0.2659 1.0000
10.250 1.3934 0.02154 0.01444 -0.0561 0.2493 1.0000
10.500 1.3986 0.02249 0.01537 -0.0532 0.2324 1.0000
10.750 1.4038 0.02352 0.01639 -0.0505 0.2165 1.0000
11.000 1.4071 0.02473 0.01757 -0.0479 0.1946 1.0000
11.250 1.4073 0.02624 0.01899 -0.0451 0.1697 1.0000
11.500 1.4030 0.02818 0.02078 -0.0423 0.1410 1.0000
11.750 1.3934 0.03071 0.02311 -0.0394 0.1112 1.0000
12.000 1.3791 0.03383 0.02596 -0.0367 0.0681 1.0000
12.250 1.3619 0.03745 0.02939 -0.0342 0.0482 1.0000
12.500 1.3538 0.04051 0.03247 -0.0326 0.0403 1.0000
12.750 1.3490 0.04340 0.03544 -0.0314 0.0361 1.0000
13.000 1.3428 0.04659 0.03871 -0.0305 0.0338 1.0000
13.250 1.3402 0.04954 0.04181 -0.0299 0.0322 1.0000
13.500 1.3358 0.05281 0.04522 -0.0296 0.0308 1.0000
13.750 1.3301 0.05638 0.04892 -0.0294 0.0297 1.0000
14.000 1.3231 0.06025 0.05290 -0.0296 0.0289 1.0000
14.250 1.3147 0.06444 0.05720 -0.0300 0.0282 1.0000
14.500 1.3032 0.06916 0.06202 -0.0306 0.0276 1.0000
14.750 1.2972 0.07326 0.06623 -0.0312 0.0270 1.0000
15.000 1.2934 0.07713 0.07022 -0.0319 0.0263 1.0000
15.250 1.2896 0.08101 0.07421 -0.0325 0.0259 1.0000
15.500 1.2866 0.08487 0.07816 -0.0332 0.0252 1.0000
15.750 1.2848 0.08849 0.08186 -0.0339 0.0247 1.0000
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Polar data table (+)
Polar graphs
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