GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 610 B AIRFOIL (goe610b-il) Reynolds number: 500,000 Max Cl/Cd: 118.04 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe610b-il-500000.txt Download as CSV file: xf-goe610b-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610 B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3116 0.11170 0.10939 -0.0346 1.0000 0.0199
-9.750 -0.3113 0.10893 0.10665 -0.0357 1.0000 0.0200
-9.500 -0.3112 0.10629 0.10405 -0.0366 1.0000 0.0200
-9.250 -0.3032 0.10192 0.09970 -0.0350 1.0000 0.0203
-9.000 -0.2984 0.09940 0.09720 -0.0343 1.0000 0.0205
-8.750 -0.2959 0.09715 0.09498 -0.0338 1.0000 0.0208
-8.500 -0.2957 0.09510 0.09297 -0.0330 1.0000 0.0211
-8.250 -0.2870 0.09224 0.09013 -0.0349 0.9987 0.0215
-8.000 -0.2677 0.08836 0.08625 -0.0399 0.9931 0.0224
-7.500 -0.2264 0.07868 0.07656 -0.0600 0.9673 0.0248
-7.250 -0.1964 0.07305 0.07088 -0.0702 0.9581 0.0249
-7.000 -0.1786 0.06823 0.06605 -0.0725 0.9503 0.0254
-6.750 -0.1504 0.06510 0.06288 -0.0767 0.9421 0.0261
-6.500 -0.1205 0.06172 0.05942 -0.0826 0.9287 0.0277
-6.250 -0.0827 0.05594 0.05343 -0.0956 0.9066 0.0306
-5.250 -0.0156 0.04334 0.04039 -0.1010 0.8581 0.0329
-5.000 0.0054 0.04104 0.03796 -0.1020 0.8492 0.0351
-4.750 0.0273 0.02137 0.01808 -0.0958 0.8204 0.0379
-4.500 0.0514 0.03092 0.02714 -0.1051 0.8325 0.0388
-4.250 0.0711 0.03016 0.02637 -0.1047 0.8245 0.0398
-4.000 0.0926 0.02907 0.02521 -0.1044 0.8165 0.0412
-3.750 0.1227 0.02776 0.02349 -0.1040 0.8089 0.0469
-3.500 0.1387 0.02277 0.01808 -0.1031 0.8009 0.0482
-3.250 0.1612 0.02173 0.01701 -0.1028 0.7929 0.0493
-3.000 0.1844 0.02085 0.01606 -0.1023 0.7834 0.0509
-2.750 0.2088 0.01982 0.01485 -0.1016 0.7745 0.0545
-2.500 0.2321 0.01798 0.01265 -0.1007 0.7646 0.0601
-2.250 0.2561 0.01724 0.01185 -0.1001 0.7525 0.0620
-2.000 0.2805 0.01653 0.01098 -0.0994 0.7377 0.0654
-1.750 0.3042 0.01567 0.00989 -0.0985 0.7199 0.0732
-1.500 0.3284 0.01532 0.00944 -0.0978 0.6998 0.0776
-1.250 0.3538 0.01326 0.00689 -0.0964 0.6825 0.0659
-1.000 0.3781 0.01333 0.00691 -0.0959 0.6659 0.0766
-0.500 0.4309 0.01134 0.00429 -0.0940 0.6420 0.0583
-0.250 0.4565 0.01088 0.00373 -0.0934 0.6314 0.0584
0.000 0.4821 0.01042 0.00320 -0.0929 0.6230 0.0590
0.250 0.5075 0.01014 0.00286 -0.0923 0.6155 0.0596
0.500 0.5331 0.00989 0.00260 -0.0918 0.6076 0.0605
0.750 0.5584 0.00976 0.00242 -0.0912 0.6004 0.0616
1.000 0.5843 0.00963 0.00230 -0.0908 0.5938 0.0637
1.250 0.6100 0.00956 0.00221 -0.0903 0.5874 0.0654
1.500 0.6360 0.00950 0.00214 -0.0898 0.5815 0.0669
1.750 0.6622 0.00946 0.00210 -0.0894 0.5756 0.0685
2.250 0.7144 0.00944 0.00208 -0.0886 0.5642 0.0734
2.500 0.7405 0.00945 0.00212 -0.0882 0.5588 0.0800
2.750 0.7662 0.00946 0.00222 -0.0877 0.5536 0.1180
3.000 0.8483 0.00787 0.00252 -0.1006 0.5441 1.0000
3.250 0.8729 0.00799 0.00261 -0.0998 0.5378 1.0000
3.500 0.8976 0.00808 0.00269 -0.0992 0.5300 1.0000
3.750 0.9219 0.00821 0.00278 -0.0984 0.5220 1.0000
4.000 0.9461 0.00832 0.00288 -0.0976 0.5123 1.0000
4.250 0.9705 0.00842 0.00300 -0.0969 0.5039 1.0000
4.500 0.9942 0.00856 0.00312 -0.0960 0.4940 1.0000
4.750 1.0180 0.00867 0.00324 -0.0952 0.4811 1.0000
5.000 1.0411 0.00882 0.00336 -0.0942 0.4612 1.0000
5.250 1.0618 0.00907 0.00351 -0.0928 0.4216 1.0000
5.500 1.0748 0.00983 0.00386 -0.0901 0.3481 1.0000
5.750 1.0918 0.01042 0.00427 -0.0882 0.3172 1.0000
6.000 1.1110 0.01087 0.00462 -0.0866 0.2962 1.0000
6.250 1.1309 0.01126 0.00496 -0.0852 0.2787 1.0000
6.500 1.1516 0.01160 0.00527 -0.0840 0.2637 1.0000
6.750 1.1712 0.01200 0.00559 -0.0825 0.2434 1.0000
7.000 1.1900 0.01244 0.00593 -0.0810 0.2175 1.0000
7.250 1.2057 0.01307 0.00635 -0.0790 0.1721 1.0000
7.500 1.2153 0.01407 0.00705 -0.0760 0.1271 1.0000
7.750 1.2311 0.01465 0.00761 -0.0740 0.1152 1.0000
8.000 1.2472 0.01519 0.00814 -0.0721 0.1041 1.0000
8.500 1.2636 0.01710 0.00964 -0.0657 0.0364 1.0000
8.750 1.2710 0.01792 0.01044 -0.0622 0.0281 1.0000
9.000 1.2809 0.01863 0.01118 -0.0592 0.0248 1.0000
9.250 1.2871 0.01960 0.01219 -0.0558 0.0221 1.0000
9.500 1.2977 0.02035 0.01303 -0.0533 0.0211 1.0000
9.750 1.3072 0.02120 0.01396 -0.0507 0.0198 1.0000
10.000 1.3152 0.02219 0.01502 -0.0482 0.0189 1.0000
10.250 1.3212 0.02335 0.01624 -0.0456 0.0179 1.0000
10.500 1.3219 0.02496 0.01794 -0.0426 0.0171 1.0000
10.750 1.3162 0.02717 0.02027 -0.0393 0.0164 1.0000
11.000 1.3273 0.02820 0.02139 -0.0378 0.0160 1.0000
11.250 1.3353 0.02952 0.02279 -0.0362 0.0154 1.0000
11.500 1.3399 0.03118 0.02455 -0.0344 0.0150 1.0000
11.750 1.3450 0.03284 0.02629 -0.0328 0.0144 1.0000
12.000 1.3482 0.03474 0.02827 -0.0312 0.0139 1.0000
12.250 1.3519 0.03665 0.03025 -0.0298 0.0136 1.0000
12.500 1.3551 0.03863 0.03232 -0.0285 0.0132 1.0000
12.750 1.3566 0.04086 0.03462 -0.0271 0.0129 1.0000
13.000 1.3571 0.04327 0.03710 -0.0256 0.0127 1.0000
13.250 1.3563 0.04618 0.04011 -0.0233 0.0122 1.0000
13.500 1.3614 0.04828 0.04233 -0.0223 0.0121 1.0000
13.750 1.3651 0.05048 0.04468 -0.0215 0.0120 1.0000
14.000 1.3676 0.05284 0.04717 -0.0209 0.0117 1.0000
14.250 1.3695 0.05536 0.04984 -0.0203 0.0115 1.0000
14.500 1.3699 0.05812 0.05274 -0.0198 0.0113 1.0000
14.750 1.3694 0.06107 0.05586 -0.0195 0.0110 1.0000
15.000 1.3683 0.06409 0.05900 -0.0196 0.0106 1.0000
15.250 1.3655 0.06750 0.06256 -0.0196 0.0105 1.0000
15.500 1.3605 0.07134 0.06657 -0.0197 0.0104 1.0000
15.750 1.3553 0.07528 0.07066 -0.0202 0.0103 1.0000
16.000 1.3479 0.07965 0.07519 -0.0210 0.0102 1.0000
16.250 1.3395 0.08428 0.07998 -0.0222 0.0101 1.0000
16.500 1.3311 0.08904 0.08489 -0.0236 0.0100 1.0000
16.750 1.3183 0.09476 0.09080 -0.0255 0.0100 1.0000
17.000 1.3092 0.09993 0.09609 -0.0275 0.0099 1.0000
17.250 1.2904 0.10721 0.10360 -0.0307 0.0100 1.0000
17.500 1.2694 0.11535 0.11197 -0.0348 0.0101 1.0000
17.750 1.2557 0.12232 0.11908 -0.0385 0.0100 1.0000
18.000 1.2332 0.13168 0.12866 -0.0440 0.0101 1.0000
18.250 1.1998 0.14445 0.14170 -0.0518 0.0105 1.0000
18.500 1.1759 0.15548 0.15291 -0.0587 0.0106 1.0000
18.750 1.1447 0.16947 0.16708 -0.0676 0.0110 1.0000
19.000 1.0979 0.19081 0.18855 -0.0802 0.0117 1.0000
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Polar data table (+)
Polar graphs
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