GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 358 AIRFOIL (goe358-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.26 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe358-il-1000000-n5.txt Download as CSV file: xf-goe358-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 358 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6454 0.08448 0.08223 -0.0548 1.0000 0.0100
-13.000 -0.7405 0.06656 0.06416 -0.0654 1.0000 0.0095
-12.750 -0.8137 0.04844 0.04576 -0.0837 0.9951 0.0091
-12.500 -0.8002 0.03518 0.03218 -0.1085 0.9898 0.0092
-12.250 -0.7649 0.02809 0.02484 -0.1239 0.9876 0.0095
-12.000 -0.7271 0.02369 0.02023 -0.1339 0.9865 0.0099
-11.750 -0.6901 0.02068 0.01702 -0.1406 0.9856 0.0102
-11.500 -0.6573 0.01890 0.01510 -0.1443 0.9838 0.0105
-11.250 -0.6264 0.01743 0.01350 -0.1470 0.9813 0.0111
-11.000 -0.5950 0.01637 0.01236 -0.1490 0.9791 0.0118
-10.750 -0.5637 0.01553 0.01143 -0.1507 0.9774 0.0124
-10.500 -0.5323 0.01483 0.01063 -0.1521 0.9759 0.0130
-10.250 -0.5027 0.01407 0.00980 -0.1532 0.9735 0.0138
-10.000 -0.4736 0.01342 0.00909 -0.1540 0.9706 0.0147
-9.750 -0.4439 0.01288 0.00848 -0.1547 0.9679 0.0157
-9.500 -0.4136 0.01236 0.00789 -0.1556 0.9656 0.0167
-9.250 -0.3846 0.01183 0.00731 -0.1561 0.9623 0.0183
-9.000 -0.3559 0.01141 0.00684 -0.1565 0.9585 0.0200
-8.750 -0.3265 0.01095 0.00636 -0.1570 0.9551 0.0225
-8.500 -0.2975 0.01059 0.00596 -0.1573 0.9513 0.0251
-8.250 -0.2690 0.01028 0.00566 -0.1575 0.9462 0.0284
-8.000 -0.2402 0.01003 0.00537 -0.1576 0.9409 0.0314
-7.750 -0.2121 0.00986 0.00522 -0.1575 0.9330 0.0346
-7.500 -0.1837 0.00970 0.00502 -0.1575 0.9250 0.0367
-7.250 -0.1555 0.00956 0.00482 -0.1573 0.9148 0.0379
-7.000 -0.1272 0.00937 0.00457 -0.1573 0.9027 0.0392
-6.750 -0.0990 0.00921 0.00435 -0.1572 0.8884 0.0410
-6.500 -0.0709 0.00911 0.00419 -0.1570 0.8713 0.0425
-6.250 -0.0431 0.00904 0.00402 -0.1568 0.8500 0.0439
-6.000 -0.0155 0.00902 0.00385 -0.1565 0.8211 0.0452
-5.750 0.0116 0.00906 0.00370 -0.1562 0.7847 0.0463
-5.500 0.0393 0.00908 0.00357 -0.1560 0.7566 0.0471
-5.250 0.0676 0.00908 0.00346 -0.1559 0.7398 0.0478
-5.000 0.0963 0.00902 0.00334 -0.1559 0.7284 0.0481
-4.500 0.1544 0.00871 0.00285 -0.1562 0.7072 0.0498
-4.250 0.1834 0.00857 0.00263 -0.1563 0.6967 0.0511
-4.000 0.2123 0.00847 0.00246 -0.1564 0.6856 0.0522
-3.750 0.2414 0.00838 0.00231 -0.1565 0.6753 0.0531
-3.500 0.2702 0.00832 0.00220 -0.1566 0.6653 0.0543
-3.250 0.2991 0.00826 0.00208 -0.1566 0.6541 0.0553
-3.000 0.3280 0.00821 0.00198 -0.1567 0.6426 0.0560
-2.750 0.3567 0.00819 0.00189 -0.1567 0.6294 0.0568
-2.500 0.3853 0.00819 0.00181 -0.1567 0.6143 0.0575
-2.250 0.4137 0.00820 0.00174 -0.1567 0.5966 0.0583
-2.000 0.4419 0.00824 0.00168 -0.1566 0.5764 0.0591
-1.750 0.4700 0.00831 0.00165 -0.1565 0.5551 0.0598
-1.500 0.4980 0.00839 0.00163 -0.1564 0.5349 0.0609
-1.250 0.5262 0.00844 0.00161 -0.1563 0.5164 0.0655
-1.000 0.5542 0.00851 0.00160 -0.1562 0.4945 0.0709
-0.750 0.5825 0.00845 0.00158 -0.1563 0.4733 0.1155
-0.500 0.6106 0.00844 0.00159 -0.1564 0.4546 0.1537
-0.250 0.6390 0.00836 0.00159 -0.1565 0.4396 0.2057
0.000 0.6672 0.00836 0.00165 -0.1565 0.4253 0.2505
0.250 0.6951 0.00844 0.00171 -0.1564 0.4113 0.2692
0.500 0.7229 0.00855 0.00179 -0.1563 0.3973 0.2821
0.750 0.7506 0.00868 0.00187 -0.1562 0.3839 0.2912
1.250 0.8062 0.00891 0.00203 -0.1559 0.3626 0.3052
1.500 0.8339 0.00902 0.00213 -0.1558 0.3546 0.3139
1.750 0.8619 0.00910 0.00221 -0.1557 0.3491 0.3203
2.000 0.8897 0.00920 0.00230 -0.1555 0.3430 0.3252
2.250 0.9173 0.00932 0.00241 -0.1554 0.3354 0.3310
2.500 0.9448 0.00944 0.00251 -0.1552 0.3280 0.3372
2.750 0.9723 0.00956 0.00264 -0.1550 0.3223 0.3448
3.000 1.0000 0.00965 0.00275 -0.1549 0.3188 0.3516
3.500 1.0552 0.00984 0.00298 -0.1545 0.3115 0.3598
3.750 1.0824 0.00997 0.00311 -0.1543 0.3072 0.3639
4.000 1.1098 0.01009 0.00324 -0.1541 0.3029 0.3679
4.250 1.1369 0.01022 0.00338 -0.1539 0.2955 0.3714
4.500 1.1636 0.01039 0.00354 -0.1536 0.2885 0.3755
4.750 1.1908 0.01050 0.00368 -0.1534 0.2832 0.3801
5.000 1.2175 0.01066 0.00384 -0.1531 0.2766 0.3848
5.250 1.2441 0.01081 0.00401 -0.1528 0.2703 0.3893
5.500 1.2702 0.01102 0.00421 -0.1525 0.2585 0.3948
5.750 1.2954 0.01131 0.00443 -0.1520 0.2382 0.3999
6.000 1.3132 0.01239 0.00509 -0.1504 0.1669 0.4041
6.250 1.3368 0.01283 0.00548 -0.1496 0.1502 0.4091
6.500 1.3608 0.01320 0.00582 -0.1490 0.1372 0.4148
6.750 1.3844 0.01361 0.00617 -0.1482 0.1215 0.4205
7.000 1.4043 0.01438 0.00673 -0.1470 0.0844 0.4270
7.250 1.4262 0.01492 0.00720 -0.1460 0.0689 0.4340
7.500 1.4490 0.01533 0.00761 -0.1451 0.0614 0.4406
7.750 1.4719 0.01572 0.00801 -0.1442 0.0564 0.4483
8.000 1.4949 0.01608 0.00839 -0.1434 0.0522 0.4560
8.250 1.5174 0.01646 0.00879 -0.1425 0.0468 0.4660
8.500 1.5389 0.01691 0.00925 -0.1415 0.0405 0.4774
8.750 1.5587 0.01747 0.00978 -0.1402 0.0311 0.4900
9.000 1.5780 0.01803 0.01034 -0.1388 0.0249 0.5050
9.250 1.5972 0.01857 0.01092 -0.1374 0.0211 0.5274
9.500 1.6173 0.01893 0.01152 -0.1363 0.0188 0.6598
9.750 1.6323 0.01902 0.01209 -0.1340 0.0170 1.0000
10.000 1.6497 0.01957 0.01266 -0.1323 0.0155 1.0000
10.250 1.6651 0.02014 0.01327 -0.1303 0.0142 1.0000
10.500 1.6778 0.02079 0.01393 -0.1277 0.0131 1.0000
10.750 1.6916 0.02140 0.01458 -0.1255 0.0124 1.0000
11.000 1.7044 0.02209 0.01531 -0.1232 0.0116 1.0000
11.250 1.7160 0.02287 0.01612 -0.1208 0.0110 1.0000
11.500 1.7271 0.02370 0.01700 -0.1184 0.0104 1.0000
11.750 1.7387 0.02454 0.01790 -0.1162 0.0100 1.0000
12.000 1.7492 0.02547 0.01889 -0.1139 0.0095 1.0000
12.250 1.7588 0.02650 0.01997 -0.1117 0.0091 1.0000
12.500 1.7668 0.02768 0.02120 -0.1094 0.0086 1.0000
12.750 1.7743 0.02897 0.02254 -0.1072 0.0083 1.0000
13.000 1.7823 0.03025 0.02389 -0.1053 0.0080 1.0000
13.250 1.7894 0.03167 0.02539 -0.1034 0.0078 1.0000
13.500 1.7955 0.03324 0.02703 -0.1015 0.0075 1.0000
13.750 1.8005 0.03498 0.02884 -0.0998 0.0073 1.0000
14.000 1.8043 0.03691 0.03086 -0.0982 0.0071 1.0000
14.250 1.8069 0.03906 0.03308 -0.0968 0.0068 1.0000
14.500 1.8079 0.04148 0.03558 -0.0955 0.0066 1.0000
14.750 1.8072 0.04417 0.03835 -0.0944 0.0065 1.0000
15.000 1.8079 0.04680 0.04108 -0.0935 0.0064 1.0000
15.250 1.8075 0.04965 0.04402 -0.0928 0.0063 1.0000
15.500 1.8057 0.05277 0.04724 -0.0922 0.0061 1.0000
15.750 1.8027 0.05611 0.05068 -0.0918 0.0060 1.0000
16.000 1.7988 0.05966 0.05433 -0.0916 0.0059 1.0000
16.250 1.7937 0.06349 0.05827 -0.0916 0.0058 1.0000
16.500 1.7875 0.06755 0.06243 -0.0918 0.0057 1.0000
16.750 1.7804 0.07183 0.06681 -0.0921 0.0056 1.0000
17.000 1.7720 0.07639 0.07147 -0.0927 0.0055 1.0000
17.250 1.7629 0.08115 0.07634 -0.0934 0.0054 1.0000
17.500 1.7528 0.08612 0.08142 -0.0943 0.0053 1.0000
17.750 1.7418 0.09128 0.08669 -0.0954 0.0053 1.0000
18.000 1.7303 0.09658 0.09210 -0.0966 0.0052 1.0000
18.250 1.7179 0.10212 0.09774 -0.0980 0.0051 1.0000
18.500 1.7051 0.10777 0.10349 -0.0996 0.0050 1.0000
18.750 1.6919 0.11352 0.10935 -0.1014 0.0050 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 358 AIRFOIL (goe358-il)