GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 510 AIRFOIL (goe510-il) Reynolds number: 500,000 Max Cl/Cd: 82.38 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe510-il-500000-n5.txt Download as CSV file: xf-goe510-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1194 0.09407 0.09140 -0.0937 0.9659 0.0283
-10.500 -0.1095 0.09097 0.08829 -0.0960 0.9630 0.0284
-9.500 -0.3443 0.03036 0.02667 -0.1300 0.9208 0.0327
-9.250 -0.3257 0.02836 0.02448 -0.1304 0.9154 0.0329
-9.000 -0.3001 0.02693 0.02290 -0.1314 0.9111 0.0332
-8.500 -0.2622 0.02421 0.01982 -0.1302 0.8962 0.0337
-8.250 -0.2454 0.02320 0.01865 -0.1287 0.8866 0.0341
-8.000 -0.2196 0.02193 0.01717 -0.1292 0.8804 0.0345
-7.750 -0.2007 0.02089 0.01594 -0.1280 0.8711 0.0351
-7.500 -0.1769 0.01967 0.01446 -0.1278 0.8627 0.0356
-7.250 -0.1544 0.01853 0.01307 -0.1272 0.8519 0.0361
-7.000 -0.1319 0.01764 0.01196 -0.1263 0.8412 0.0365
-6.750 -0.1069 0.01690 0.01099 -0.1259 0.8316 0.0369
-6.500 -0.0839 0.01632 0.01022 -0.1250 0.8202 0.0372
-6.250 -0.0616 0.01566 0.00944 -0.1240 0.8090 0.0376
-6.000 -0.0380 0.01526 0.00894 -0.1232 0.7962 0.0380
-5.750 -0.0151 0.01495 0.00853 -0.1222 0.7839 0.0383
-5.500 0.0073 0.01465 0.00815 -0.1210 0.7726 0.0387
-5.250 0.0301 0.01439 0.00780 -0.1199 0.7615 0.0391
-5.000 0.0525 0.01416 0.00748 -0.1187 0.7494 0.0396
-4.750 0.0743 0.01391 0.00714 -0.1173 0.7362 0.0401
-4.500 0.0958 0.01370 0.00682 -0.1159 0.7219 0.0408
-4.250 0.1166 0.01343 0.00643 -0.1143 0.7067 0.0413
-4.000 0.1372 0.01322 0.00609 -0.1127 0.6914 0.0418
-3.750 0.1578 0.01302 0.00578 -0.1111 0.6775 0.0422
-3.250 0.1997 0.01274 0.00529 -0.1079 0.6518 0.0430
-3.000 0.2198 0.01243 0.00493 -0.1063 0.6396 0.0437
-2.750 0.2400 0.01228 0.00472 -0.1046 0.6280 0.0442
-2.500 0.2606 0.01218 0.00456 -0.1030 0.6158 0.0448
-2.250 0.2819 0.01208 0.00442 -0.1015 0.6055 0.0456
-2.000 0.3021 0.01202 0.00430 -0.0998 0.5948 0.0464
-1.750 0.3228 0.01192 0.00415 -0.0982 0.5832 0.0472
-1.500 0.3416 0.01184 0.00401 -0.0962 0.5711 0.0478
-1.250 0.3594 0.01178 0.00388 -0.0940 0.5581 0.0485
-1.000 0.3772 0.01174 0.00377 -0.0918 0.5441 0.0491
-0.750 0.3952 0.01172 0.00368 -0.0896 0.5284 0.0496
-0.500 0.4121 0.01166 0.00356 -0.0872 0.5118 0.0504
-0.250 0.4285 0.01163 0.00346 -0.0848 0.4949 0.0513
0.000 0.4461 0.01165 0.00342 -0.0826 0.4800 0.0525
0.250 0.4648 0.01169 0.00340 -0.0807 0.4677 0.0537
0.500 0.4833 0.01175 0.00340 -0.0787 0.4560 0.0550
0.750 0.5027 0.01182 0.00342 -0.0770 0.4460 0.0560
1.000 0.5227 0.01188 0.00343 -0.0753 0.4381 0.0569
1.250 0.5429 0.01195 0.00346 -0.0737 0.4306 0.0579
1.500 0.5625 0.01201 0.00348 -0.0720 0.4240 0.0598
1.750 0.5834 0.01205 0.00351 -0.0706 0.4175 0.0619
2.000 0.6036 0.01213 0.00357 -0.0690 0.4118 0.0648
2.250 0.6238 0.01221 0.00363 -0.0675 0.4064 0.0681
2.500 0.6449 0.01224 0.00369 -0.0661 0.4021 0.0763
2.750 0.6622 0.01212 0.00381 -0.0640 0.3972 0.1589
3.000 0.6808 0.01217 0.00397 -0.0623 0.3925 0.2050
3.250 0.7019 0.01225 0.00410 -0.0609 0.3887 0.2299
3.500 0.7234 0.01233 0.00422 -0.0597 0.3844 0.2479
3.750 0.7439 0.01245 0.00437 -0.0583 0.3797 0.2653
4.000 0.7637 0.01259 0.00452 -0.0568 0.3758 0.2779
4.250 0.7844 0.01272 0.00465 -0.0555 0.3724 0.2874
4.500 0.8060 0.01281 0.00479 -0.0543 0.3688 0.2990
4.750 0.8265 0.01292 0.00494 -0.0530 0.3644 0.3124
5.000 0.8460 0.01306 0.00510 -0.0515 0.3603 0.3296
5.250 0.8646 0.01321 0.00528 -0.0498 0.3562 0.3489
5.500 0.8845 0.01325 0.00545 -0.0484 0.3527 0.3858
6.000 1.0535 0.01300 0.00653 -0.0740 0.3393 0.9911
6.250 1.0859 0.01328 0.00681 -0.0753 0.3340 0.9983
6.500 1.1163 0.01355 0.00706 -0.0763 0.3292 1.0000
6.750 1.1305 0.01378 0.00727 -0.0738 0.3252 1.0000
7.000 1.1464 0.01399 0.00748 -0.0717 0.3208 1.0000
7.250 1.1624 0.01421 0.00770 -0.0696 0.3153 1.0000
7.500 1.1755 0.01454 0.00798 -0.0671 0.3073 1.0000
7.750 1.1921 0.01479 0.00823 -0.0652 0.3003 1.0000
8.000 1.2051 0.01518 0.00856 -0.0628 0.2917 1.0000
8.250 1.2210 0.01550 0.00888 -0.0609 0.2825 1.0000
8.500 1.2346 0.01593 0.00927 -0.0587 0.2738 1.0000
8.750 1.2479 0.01641 0.00969 -0.0565 0.2628 1.0000
9.000 1.2605 0.01694 0.01016 -0.0543 0.2499 1.0000
9.250 1.2728 0.01751 0.01069 -0.0521 0.2388 1.0000
9.500 1.2847 0.01813 0.01126 -0.0499 0.2283 1.0000
9.750 1.2975 0.01874 0.01184 -0.0479 0.2184 1.0000
10.000 1.3090 0.01943 0.01249 -0.0458 0.2072 1.0000
10.250 1.3183 0.02027 0.01327 -0.0436 0.1940 1.0000
10.500 1.3223 0.02144 0.01431 -0.0407 0.1724 1.0000
10.750 1.3281 0.02256 0.01534 -0.0383 0.1556 1.0000
11.000 1.3264 0.02419 0.01681 -0.0351 0.1302 1.0000
11.250 1.3245 0.02592 0.01842 -0.0322 0.1086 1.0000
11.500 1.3196 0.02795 0.02034 -0.0292 0.0877 1.0000
11.750 1.3123 0.03027 0.02255 -0.0263 0.0657 1.0000
12.250 1.2913 0.03594 0.02813 -0.0210 0.0208 1.0000
12.500 1.2963 0.03770 0.02995 -0.0198 0.0191 1.0000
12.750 1.3006 0.03959 0.03190 -0.0187 0.0178 1.0000
13.000 1.3056 0.04146 0.03384 -0.0178 0.0170 1.0000
13.250 1.3101 0.04344 0.03590 -0.0170 0.0163 1.0000
13.500 1.3134 0.04560 0.03813 -0.0162 0.0156 1.0000
13.750 1.3162 0.04788 0.04049 -0.0156 0.0153 1.0000
14.000 1.3167 0.05044 0.04314 -0.0150 0.0147 1.0000
14.250 1.3158 0.05322 0.04600 -0.0145 0.0143 1.0000
14.500 1.3149 0.05607 0.04895 -0.0141 0.0139 1.0000
14.750 1.3152 0.05885 0.05182 -0.0139 0.0136 1.0000
15.000 1.3141 0.06186 0.05491 -0.0138 0.0134 1.0000
15.250 1.3127 0.06494 0.05809 -0.0138 0.0130 1.0000
15.500 1.3092 0.06834 0.06159 -0.0138 0.0128 1.0000
15.750 1.3045 0.07198 0.06532 -0.0141 0.0125 1.0000
16.000 1.2998 0.07570 0.06914 -0.0144 0.0123 1.0000
16.250 1.2941 0.07959 0.07312 -0.0149 0.0121 1.0000
16.500 1.2873 0.08366 0.07728 -0.0155 0.0119 1.0000
16.750 1.2791 0.08798 0.08170 -0.0162 0.0116 1.0000
17.000 1.2718 0.09225 0.08607 -0.0169 0.0116 1.0000
17.250 1.2630 0.09675 0.09066 -0.0178 0.0115 1.0000
17.500 1.2513 0.10172 0.09573 -0.0189 0.0113 1.0000
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Polar data table (+)
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