GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 513 AIRFOIL (goe513-il) Reynolds number: 500,000 Max Cl/Cd: 66.11 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe513-il-500000-n5.txt Download as CSV file: xf-goe513-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 513 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5544 0.05620 0.05275 -0.1187 0.9747 0.0249
-14.000 -0.5920 0.04298 0.03911 -0.1343 0.9717 0.0250
-13.750 -0.5987 0.03867 0.03457 -0.1378 0.9698 0.0250
-13.500 -0.6026 0.03616 0.03190 -0.1376 0.9666 0.0252
-13.250 -0.6051 0.03416 0.02974 -0.1361 0.9617 0.0253
-13.000 -0.5992 0.03221 0.02762 -0.1356 0.9590 0.0255
-12.750 -0.5875 0.03058 0.02583 -0.1353 0.9570 0.0257
-12.500 -0.5733 0.02898 0.02406 -0.1351 0.9555 0.0260
-12.250 -0.5748 0.02806 0.02302 -0.1309 0.9499 0.0261
-12.000 -0.5661 0.02699 0.02180 -0.1286 0.9459 0.0263
-11.750 -0.5479 0.02580 0.02046 -0.1280 0.9433 0.0265
-11.500 -0.5244 0.02488 0.01938 -0.1282 0.9414 0.0269
-11.250 -0.5003 0.02390 0.01825 -0.1283 0.9398 0.0270
-11.000 -0.5108 0.02343 0.01772 -0.1210 0.9305 0.0272
-10.750 -0.4899 0.02237 0.01658 -0.1204 0.9272 0.0273
-10.500 -0.4641 0.02144 0.01558 -0.1206 0.9247 0.0275
-10.250 -0.4651 0.02107 0.01518 -0.1149 0.9157 0.0277
-10.000 -0.4446 0.02039 0.01445 -0.1138 0.9111 0.0279
-9.750 -0.4173 0.01967 0.01367 -0.1140 0.9078 0.0281
-9.500 -0.4164 0.01934 0.01330 -0.1086 0.8971 0.0283
-9.250 -0.3877 0.01868 0.01257 -0.1090 0.8923 0.0285
-9.000 -0.3773 0.01825 0.01208 -0.1054 0.8811 0.0287
-8.750 -0.3517 0.01766 0.01142 -0.1051 0.8724 0.0290
-8.500 -0.3257 0.01711 0.01079 -0.1048 0.8622 0.0293
-8.250 -0.2998 0.01662 0.01022 -0.1044 0.8509 0.0297
-8.000 -0.2706 0.01614 0.00963 -0.1048 0.8380 0.0301
-7.750 -0.2427 0.01568 0.00906 -0.1048 0.8225 0.0305
-7.500 -0.2174 0.01532 0.00856 -0.1042 0.8052 0.0308
-7.250 -0.1949 0.01502 0.00813 -0.1030 0.7884 0.0311
-7.000 -0.1743 0.01476 0.00774 -0.1014 0.7730 0.0313
-6.750 -0.1566 0.01441 0.00731 -0.0993 0.7590 0.0316
-6.500 -0.1381 0.01414 0.00697 -0.0973 0.7470 0.0319
-6.250 -0.1194 0.01393 0.00668 -0.0953 0.7348 0.0323
-6.000 -0.1002 0.01371 0.00641 -0.0934 0.7240 0.0326
-5.750 -0.0809 0.01353 0.00616 -0.0915 0.7137 0.0330
-5.500 -0.0614 0.01335 0.00592 -0.0897 0.7034 0.0335
-5.250 -0.0423 0.01319 0.00570 -0.0877 0.6920 0.0339
-5.000 -0.0237 0.01304 0.00548 -0.0856 0.6799 0.0344
-4.750 -0.0054 0.01289 0.00528 -0.0835 0.6650 0.0349
-4.500 0.0105 0.01280 0.00509 -0.0808 0.6449 0.0354
-4.250 0.0220 0.01279 0.00494 -0.0772 0.6125 0.0359
-4.000 0.0270 0.01282 0.00479 -0.0722 0.5741 0.0364
-3.750 0.0344 0.01283 0.00466 -0.0678 0.5511 0.0371
-3.500 0.0473 0.01280 0.00454 -0.0645 0.5363 0.0378
-3.250 0.0636 0.01276 0.00443 -0.0619 0.5253 0.0386
-2.750 0.0999 0.01267 0.00423 -0.0576 0.5091 0.0404
-2.500 0.1186 0.01261 0.00412 -0.0556 0.5016 0.0419
-2.250 0.1370 0.01258 0.00404 -0.0535 0.4938 0.0437
-2.000 0.1569 0.01253 0.00397 -0.0517 0.4867 0.0459
-1.750 0.1746 0.01252 0.00392 -0.0495 0.4783 0.0493
-1.500 0.1946 0.01244 0.00385 -0.0478 0.4714 0.0566
-1.250 0.2119 0.01209 0.00372 -0.0457 0.4647 0.1163
-1.000 0.2283 0.01190 0.00378 -0.0434 0.4600 0.1864
-0.750 0.2480 0.01191 0.00382 -0.0416 0.4556 0.2028
-0.500 0.2690 0.01193 0.00384 -0.0401 0.4510 0.2149
-0.250 0.2891 0.01196 0.00388 -0.0384 0.4462 0.2235
0.000 0.3087 0.01202 0.00392 -0.0366 0.4414 0.2300
0.250 0.3287 0.01208 0.00395 -0.0349 0.4368 0.2363
0.500 0.3494 0.01210 0.00400 -0.0334 0.4321 0.2423
0.750 0.3692 0.01217 0.00404 -0.0317 0.4262 0.2480
1.000 0.3882 0.01227 0.00409 -0.0298 0.4206 0.2531
1.250 0.4086 0.01229 0.00415 -0.0282 0.4149 0.2598
1.500 0.4287 0.01236 0.00420 -0.0266 0.4092 0.2652
1.750 0.4473 0.01246 0.00426 -0.0248 0.4035 0.2686
2.000 0.4676 0.01253 0.00431 -0.0232 0.3982 0.2715
2.250 0.4874 0.01259 0.00438 -0.0216 0.3922 0.2755
2.500 0.5057 0.01269 0.00446 -0.0197 0.3859 0.2795
2.750 0.5257 0.01278 0.00454 -0.0182 0.3801 0.2837
3.000 0.5450 0.01290 0.00463 -0.0165 0.3730 0.2879
3.250 0.5627 0.01303 0.00474 -0.0146 0.3660 0.2927
3.500 0.5819 0.01314 0.00485 -0.0129 0.3580 0.2985
4.000 0.6192 0.01344 0.00511 -0.0095 0.3431 0.3098
4.250 0.6367 0.01361 0.00527 -0.0077 0.3354 0.3173
4.500 0.6552 0.01378 0.00543 -0.0060 0.3283 0.3247
4.750 0.6732 0.01395 0.00560 -0.0043 0.3203 0.3341
5.000 0.6911 0.01414 0.00580 -0.0026 0.3132 0.3468
5.250 0.7092 0.01430 0.00600 -0.0010 0.3056 0.3654
5.500 0.7255 0.01446 0.00623 0.0009 0.2985 0.4074
6.000 0.9551 0.01500 0.00811 -0.0382 0.2686 0.9777
6.250 0.9798 0.01541 0.00849 -0.0381 0.2633 0.9826
6.500 1.0147 0.01578 0.00883 -0.0402 0.2574 0.9855
6.750 1.0462 0.01621 0.00922 -0.0416 0.2522 0.9890
7.000 1.0748 0.01663 0.00962 -0.0425 0.2480 0.9919
7.250 1.1106 0.01699 0.00998 -0.0448 0.2437 0.9946
7.500 1.1450 0.01735 0.01032 -0.0470 0.2395 0.9972
7.750 1.1768 0.01780 0.01073 -0.0487 0.2352 0.9993
8.000 1.1985 0.01819 0.01113 -0.0482 0.2323 1.0000
8.250 1.2130 0.01852 0.01148 -0.0462 0.2301 1.0000
8.500 1.2270 0.01888 0.01186 -0.0441 0.2280 1.0000
8.750 1.2404 0.01928 0.01228 -0.0420 0.2261 1.0000
9.000 1.2535 0.01972 0.01273 -0.0399 0.2240 1.0000
9.250 1.2657 0.02020 0.01322 -0.0377 0.2218 1.0000
9.500 1.2774 0.02072 0.01375 -0.0355 0.2198 1.0000
9.750 1.2885 0.02130 0.01433 -0.0332 0.2176 1.0000
10.000 1.3013 0.02182 0.01488 -0.0313 0.2160 1.0000
10.250 1.3156 0.02229 0.01540 -0.0296 0.2143 1.0000
10.500 1.3289 0.02282 0.01597 -0.0278 0.2129 1.0000
10.750 1.3418 0.02338 0.01658 -0.0261 0.2114 1.0000
11.000 1.3541 0.02400 0.01723 -0.0243 0.2098 1.0000
11.250 1.3660 0.02466 0.01793 -0.0225 0.2083 1.0000
11.500 1.3773 0.02538 0.01867 -0.0208 0.2066 1.0000
11.750 1.3866 0.02624 0.01954 -0.0189 0.2041 1.0000
12.000 1.3966 0.02709 0.02042 -0.0171 0.2028 1.0000
12.250 1.4067 0.02796 0.02133 -0.0155 0.2002 1.0000
12.500 1.4199 0.02867 0.02210 -0.0142 0.1983 1.0000
12.750 1.4315 0.02949 0.02298 -0.0128 0.1966 1.0000
13.000 1.4423 0.03039 0.02393 -0.0115 0.1943 1.0000
13.250 1.4520 0.03141 0.02498 -0.0101 0.1918 1.0000
13.500 1.4601 0.03255 0.02616 -0.0086 0.1898 1.0000
13.750 1.4670 0.03382 0.02745 -0.0072 0.1876 1.0000
14.000 1.4743 0.03508 0.02875 -0.0059 0.1855 1.0000
14.250 1.4854 0.03609 0.02984 -0.0049 0.1841 1.0000
14.500 1.4952 0.03724 0.03105 -0.0039 0.1810 1.0000
14.750 1.5039 0.03847 0.03236 -0.0029 0.1799 1.0000
15.000 1.5107 0.03990 0.03385 -0.0018 0.1774 1.0000
15.250 1.5155 0.04154 0.03552 -0.0008 0.1749 1.0000
15.500 1.5185 0.04336 0.03737 0.0003 0.1726 1.0000
15.750 1.5248 0.04493 0.03902 0.0011 0.1702 1.0000
16.000 1.5313 0.04653 0.04070 0.0018 0.1678 1.0000
16.250 1.5349 0.04844 0.04267 0.0025 0.1641 1.0000
16.500 1.5370 0.05054 0.04482 0.0032 0.1620 1.0000
16.750 1.5337 0.05326 0.04757 0.0038 0.1584 1.0000
17.000 1.5374 0.05530 0.04970 0.0041 0.1544 1.0000
17.250 1.5368 0.05786 0.05231 0.0045 0.1505 1.0000
17.500 1.5292 0.06126 0.05575 0.0047 0.1460 1.0000
17.750 1.5283 0.06393 0.05849 0.0048 0.1420 1.0000
18.000 1.5199 0.06751 0.06210 0.0049 0.1363 1.0000
18.250 1.5113 0.07112 0.06577 0.0048 0.1322 1.0000
18.500 1.5007 0.07503 0.06973 0.0047 0.1260 1.0000
18.750 1.4769 0.08063 0.07533 0.0042 0.1161 1.0000
19.000 1.4698 0.08418 0.07895 0.0039 0.1136 1.0000
19.250 1.4449 0.09012 0.08491 0.0031 0.1044 1.0000
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Polar data table (+)
Polar graphs
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