GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 510 AIRFOIL (goe510-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.86 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe510-il-1000000.txt Download as CSV file: xf-goe510-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 510 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0442 0.08892 0.08706 -0.1031 0.9719 0.0323
-9.750 -0.0296 0.08565 0.08378 -0.1065 0.9710 0.0329
-9.000 -0.0327 0.06822 0.06635 -0.1218 0.9602 0.0358
-8.750 -0.0170 0.06491 0.06304 -0.1261 0.9579 0.0359
-8.500 -0.2108 0.02177 0.01822 -0.1422 0.9230 0.0346
-8.250 -0.2005 0.02013 0.01631 -0.1396 0.9141 0.0349
-8.000 -0.1783 0.01928 0.01526 -0.1389 0.9074 0.0352
-7.750 -0.1691 0.01712 0.01277 -0.1362 0.8975 0.0357
-7.500 -0.1495 0.01619 0.01172 -0.1349 0.8886 0.0361
-7.250 -0.1237 0.01566 0.01110 -0.1347 0.8803 0.0364
-7.000 -0.1014 0.01533 0.01071 -0.1336 0.8700 0.0367
-6.750 -0.0760 0.01511 0.01041 -0.1330 0.8592 0.0372
-6.500 -0.0524 0.01477 0.00998 -0.1322 0.8479 0.0376
-6.250 -0.0307 0.01435 0.00947 -0.1309 0.8379 0.0380
-6.000 -0.0079 0.01391 0.00890 -0.1299 0.8281 0.0385
-5.750 0.0135 0.01342 0.00829 -0.1285 0.8178 0.0389
-5.500 0.0358 0.01305 0.00781 -0.1272 0.8079 0.0394
-5.000 0.0798 0.01247 0.00700 -0.1245 0.7855 0.0403
-4.750 0.1020 0.01232 0.00676 -0.1232 0.7741 0.0406
-4.500 0.1220 0.01156 0.00586 -0.1216 0.7624 0.0412
-4.250 0.1431 0.01116 0.00541 -0.1201 0.7497 0.0418
-4.000 0.1643 0.01099 0.00519 -0.1186 0.7361 0.0424
-3.750 0.1849 0.01088 0.00503 -0.1169 0.7214 0.0430
-3.500 0.2048 0.01078 0.00484 -0.1151 0.7054 0.0436
-3.250 0.2245 0.01063 0.00461 -0.1133 0.6902 0.0441
-3.000 0.2442 0.01050 0.00440 -0.1114 0.6759 0.0447
-2.750 0.2643 0.01040 0.00422 -0.1096 0.6621 0.0454
-2.500 0.2850 0.01030 0.00406 -0.1080 0.6490 0.0460
-2.250 0.3057 0.01024 0.00393 -0.1063 0.6371 0.0464
-2.000 0.3253 0.01023 0.00384 -0.1044 0.6254 0.0468
-1.750 0.3435 0.00983 0.00340 -0.1023 0.6147 0.0478
-1.500 0.3617 0.00968 0.00322 -0.1001 0.6041 0.0488
-1.250 0.3799 0.00963 0.00313 -0.0980 0.5922 0.0497
-1.000 0.3999 0.00956 0.00302 -0.0962 0.5799 0.0506
-0.750 0.4194 0.00952 0.00294 -0.0943 0.5673 0.0516
-0.500 0.4380 0.00950 0.00286 -0.0922 0.5523 0.0525
-0.250 0.4561 0.00951 0.00280 -0.0901 0.5356 0.0531
0.000 0.4739 0.00958 0.00278 -0.0879 0.5157 0.0538
0.250 0.4909 0.00961 0.00271 -0.0855 0.4955 0.0545
0.500 0.5080 0.00961 0.00263 -0.0832 0.4777 0.0562
0.750 0.5268 0.00968 0.00263 -0.0813 0.4631 0.0578
1.000 0.5460 0.00976 0.00266 -0.0794 0.4511 0.0594
1.250 0.5655 0.00984 0.00269 -0.0777 0.4409 0.0608
1.500 0.5863 0.00990 0.00271 -0.0762 0.4335 0.0621
1.750 0.6066 0.00994 0.00272 -0.0745 0.4265 0.0646
2.000 0.6265 0.01001 0.00277 -0.0729 0.4201 0.0683
2.250 0.6485 0.01003 0.00280 -0.0716 0.4155 0.0725
2.500 0.6654 0.00989 0.00288 -0.0694 0.4103 0.1560
2.750 0.6827 0.00991 0.00304 -0.0673 0.4044 0.2197
3.000 0.7046 0.00995 0.00314 -0.0661 0.4008 0.2447
3.250 0.7265 0.01001 0.00324 -0.0649 0.3968 0.2623
3.500 0.7476 0.01012 0.00335 -0.0635 0.3923 0.2744
3.750 0.7674 0.01026 0.00348 -0.0620 0.3875 0.2880
4.000 0.7899 0.01032 0.00358 -0.0609 0.3840 0.2990
4.250 0.8120 0.01040 0.00368 -0.0598 0.3801 0.3089
4.500 0.8326 0.01050 0.00380 -0.0584 0.3763 0.3222
4.750 0.8519 0.01063 0.00394 -0.0568 0.3720 0.3371
5.000 0.8721 0.01073 0.00409 -0.0554 0.3684 0.3577
5.250 0.8892 0.01057 0.00422 -0.0533 0.3654 0.4780
5.500 1.0317 0.01014 0.00496 -0.0791 0.3557 0.9872
5.750 1.0704 0.01043 0.00522 -0.0816 0.3512 0.9938
6.000 1.1131 0.01062 0.00541 -0.0851 0.3468 0.9973
6.250 1.1533 0.01087 0.00561 -0.0882 0.3398 0.9993
6.500 1.1816 0.01106 0.00578 -0.0886 0.3337 1.0000
6.750 1.1958 0.01119 0.00590 -0.0860 0.3278 1.0000
7.000 1.2076 0.01139 0.00607 -0.0830 0.3223 1.0000
7.250 1.2220 0.01156 0.00623 -0.0805 0.3163 1.0000
7.500 1.2357 0.01179 0.00641 -0.0779 0.3074 1.0000
7.750 1.2503 0.01202 0.00662 -0.0755 0.2991 1.0000
8.000 1.2637 0.01232 0.00687 -0.0730 0.2901 1.0000
8.250 1.2798 0.01256 0.00710 -0.0710 0.2836 1.0000
8.500 1.2936 0.01293 0.00741 -0.0686 0.2735 1.0000
8.750 1.3095 0.01323 0.00770 -0.0667 0.2654 1.0000
9.000 1.3232 0.01365 0.00807 -0.0644 0.2558 1.0000
9.250 1.3376 0.01408 0.00844 -0.0624 0.2447 1.0000
9.500 1.3522 0.01452 0.00885 -0.0604 0.2350 1.0000
9.750 1.3650 0.01506 0.00933 -0.0582 0.2239 1.0000
10.000 1.3769 0.01567 0.00987 -0.0559 0.2113 1.0000
10.250 1.3870 0.01638 0.01051 -0.0534 0.1960 1.0000
10.500 1.3918 0.01740 0.01137 -0.0503 0.1715 1.0000
10.750 1.3894 0.01883 0.01259 -0.0464 0.1404 1.0000
11.000 1.3784 0.02083 0.01434 -0.0417 0.1044 1.0000
11.250 1.3639 0.02318 0.01647 -0.0369 0.0690 1.0000
11.500 1.3430 0.02617 0.01929 -0.0320 0.0266 1.0000
11.750 1.3470 0.02766 0.02081 -0.0299 0.0210 1.0000
12.000 1.3545 0.02897 0.02215 -0.0282 0.0194 1.0000
12.250 1.3634 0.03021 0.02344 -0.0269 0.0186 1.0000
12.500 1.3702 0.03167 0.02495 -0.0254 0.0177 1.0000
12.750 1.3754 0.03329 0.02662 -0.0240 0.0169 1.0000
13.000 1.3792 0.03510 0.02850 -0.0226 0.0163 1.0000
13.250 1.3855 0.03676 0.03021 -0.0215 0.0159 1.0000
13.500 1.3910 0.03855 0.03206 -0.0205 0.0155 1.0000
13.750 1.3961 0.04042 0.03399 -0.0196 0.0151 1.0000
14.000 1.3988 0.04257 0.03621 -0.0187 0.0146 1.0000
14.250 1.4007 0.04487 0.03857 -0.0179 0.0143 1.0000
14.500 1.4002 0.04749 0.04127 -0.0172 0.0140 1.0000
14.750 1.3995 0.05021 0.04407 -0.0166 0.0138 1.0000
15.000 1.3889 0.05409 0.04806 -0.0160 0.0134 1.0000
15.250 1.3891 0.05685 0.05090 -0.0158 0.0132 1.0000
15.500 1.3874 0.05989 0.05401 -0.0156 0.0131 1.0000
15.750 1.3848 0.06311 0.05731 -0.0156 0.0129 1.0000
16.000 1.3803 0.06660 0.06090 -0.0156 0.0128 1.0000
16.250 1.3746 0.07033 0.06471 -0.0158 0.0126 1.0000
16.500 1.3689 0.07412 0.06860 -0.0161 0.0124 1.0000
16.750 1.3615 0.07822 0.07278 -0.0166 0.0123 1.0000
17.000 1.3549 0.08223 0.07688 -0.0171 0.0121 1.0000
17.250 1.3477 0.08639 0.08112 -0.0178 0.0118 1.0000
17.500 1.3393 0.09076 0.08557 -0.0186 0.0117 1.0000
17.750 1.3293 0.09541 0.09032 -0.0195 0.0117 1.0000
18.000 1.3204 0.09989 0.09487 -0.0204 0.0114 1.0000
18.250 1.3092 0.10479 0.09986 -0.0215 0.0114 1.0000
18.500 1.2987 0.10963 0.10479 -0.0227 0.0112 1.0000
18.750 1.2860 0.11488 0.11013 -0.0242 0.0111 1.0000
19.000 1.2687 0.12088 0.11623 -0.0259 0.0109 1.0000
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