GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 615 AIRFOIL (goe615-il) Reynolds number: 500,000 Max Cl/Cd: 93.51 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe615-il-500000-n5.txt Download as CSV file: xf-goe615-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 615 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3717 0.02653 0.02228 -0.1340 0.8596 0.0275
-9.750 -0.3679 0.02389 0.01919 -0.1322 0.8489 0.0279
-9.500 -0.3536 0.02238 0.01738 -0.1310 0.8402 0.0283
-9.250 -0.3337 0.02165 0.01657 -0.1300 0.8318 0.0286
-9.000 -0.3124 0.02104 0.01585 -0.1292 0.8240 0.0288
-8.750 -0.2912 0.02038 0.01509 -0.1283 0.8161 0.0290
-8.500 -0.2697 0.01972 0.01428 -0.1275 0.8079 0.0293
-8.250 -0.2479 0.01905 0.01348 -0.1266 0.8000 0.0296
-8.000 -0.2259 0.01836 0.01265 -0.1257 0.7916 0.0299
-7.750 -0.2033 0.01772 0.01186 -0.1249 0.7840 0.0303
-7.500 -0.1805 0.01706 0.01105 -0.1240 0.7759 0.0307
-7.250 -0.1573 0.01642 0.01026 -0.1232 0.7686 0.0311
-7.000 -0.1335 0.01588 0.00958 -0.1224 0.7604 0.0317
-6.750 -0.1094 0.01540 0.00893 -0.1217 0.7527 0.0321
-6.500 -0.0849 0.01493 0.00834 -0.1210 0.7444 0.0324
-6.250 -0.0612 0.01438 0.00769 -0.1202 0.7362 0.0328
-6.000 -0.0364 0.01397 0.00723 -0.1195 0.7274 0.0332
-5.750 -0.0117 0.01366 0.00685 -0.1188 0.7186 0.0335
-5.500 0.0135 0.01336 0.00650 -0.1182 0.7088 0.0340
-5.250 0.0384 0.01309 0.00616 -0.1174 0.6988 0.0344
-5.000 0.0634 0.01283 0.00582 -0.1167 0.6877 0.0349
-4.750 0.0884 0.01257 0.00549 -0.1160 0.6768 0.0355
-4.500 0.1133 0.01235 0.00517 -0.1153 0.6661 0.0360
-4.250 0.1385 0.01215 0.00490 -0.1146 0.6544 0.0367
-4.000 0.1637 0.01198 0.00464 -0.1139 0.6432 0.0373
-3.750 0.1880 0.01174 0.00434 -0.1130 0.6320 0.0380
-3.500 0.2128 0.01156 0.00412 -0.1123 0.6199 0.0386
-3.250 0.2375 0.01144 0.00394 -0.1115 0.6066 0.0393
-3.000 0.2620 0.01135 0.00377 -0.1107 0.5934 0.0401
-2.750 0.2865 0.01127 0.00361 -0.1098 0.5815 0.0411
-2.500 0.3118 0.01118 0.00346 -0.1092 0.5719 0.0421
-2.250 0.3370 0.01113 0.00334 -0.1085 0.5638 0.0430
-2.000 0.3624 0.01100 0.00319 -0.1079 0.5561 0.0444
-1.500 0.4136 0.01089 0.00302 -0.1067 0.5433 0.0475
-1.250 0.4392 0.01085 0.00294 -0.1061 0.5364 0.0491
-1.000 0.4643 0.01081 0.00285 -0.1054 0.5303 0.0510
-0.750 0.4905 0.01074 0.00279 -0.1049 0.5247 0.0535
-0.500 0.5163 0.01072 0.00274 -0.1044 0.5192 0.0563
-0.250 0.5416 0.01071 0.00271 -0.1038 0.5144 0.0605
0.250 0.5933 0.01056 0.00268 -0.1028 0.5055 0.0942
0.500 0.6175 0.01034 0.00271 -0.1021 0.5009 0.1808
1.000 0.6673 0.01019 0.00282 -0.1008 0.4914 0.2784
1.250 0.6920 0.01009 0.00288 -0.1002 0.4861 0.3389
1.500 0.7153 0.00996 0.00296 -0.0993 0.4808 0.4243
1.750 0.7369 0.00971 0.00306 -0.0981 0.4756 0.5542
2.000 0.7548 0.00932 0.00316 -0.0960 0.4692 0.7216
2.500 0.8687 0.00933 0.00351 -0.1084 0.4369 1.0000
2.750 0.8893 0.00951 0.00358 -0.1069 0.4191 1.0000
3.000 0.9082 0.00975 0.00369 -0.1051 0.3971 1.0000
3.250 0.9258 0.01005 0.00384 -0.1031 0.3724 1.0000
3.500 0.9428 0.01039 0.00403 -0.1010 0.3506 1.0000
4.000 0.9784 0.01104 0.00446 -0.0971 0.3187 1.0000
4.250 0.9974 0.01132 0.00467 -0.0954 0.3081 1.0000
4.500 1.0156 0.01162 0.00489 -0.0936 0.2980 1.0000
4.750 1.0347 0.01186 0.00509 -0.0919 0.2891 1.0000
5.000 1.0511 0.01215 0.00532 -0.0897 0.2802 1.0000
5.250 1.0693 0.01239 0.00553 -0.0879 0.2721 1.0000
5.750 1.1050 0.01293 0.00600 -0.0842 0.2584 1.0000
6.000 1.1229 0.01322 0.00626 -0.0825 0.2515 1.0000
6.250 1.1404 0.01354 0.00654 -0.0807 0.2436 1.0000
6.500 1.1575 0.01388 0.00684 -0.0789 0.2350 1.0000
6.750 1.1750 0.01422 0.00715 -0.0772 0.2279 1.0000
7.000 1.1919 0.01459 0.00749 -0.0754 0.2197 1.0000
7.250 1.2088 0.01497 0.00785 -0.0737 0.2132 1.0000
7.500 1.2256 0.01537 0.00823 -0.0721 0.2056 1.0000
7.750 1.2418 0.01581 0.00864 -0.0704 0.1993 1.0000
8.000 1.2579 0.01627 0.00908 -0.0687 0.1914 1.0000
8.250 1.2726 0.01681 0.00959 -0.0669 0.1830 1.0000
8.500 1.2866 0.01740 0.01015 -0.0651 0.1740 1.0000
8.750 1.2996 0.01807 0.01076 -0.0632 0.1629 1.0000
9.000 1.3127 0.01876 0.01143 -0.0615 0.1543 1.0000
9.250 1.3232 0.01962 0.01223 -0.0595 0.1419 1.0000
9.500 1.3302 0.02072 0.01323 -0.0572 0.1239 1.0000
9.750 1.3200 0.02296 0.01519 -0.0533 0.0804 1.0000
10.000 1.3225 0.02452 0.01667 -0.0510 0.0660 1.0000
10.250 1.3332 0.02558 0.01775 -0.0496 0.0633 1.0000
10.500 1.3435 0.02670 0.01890 -0.0482 0.0611 1.0000
10.750 1.3534 0.02789 0.02012 -0.0469 0.0588 1.0000
11.000 1.3640 0.02906 0.02132 -0.0457 0.0571 1.0000
11.250 1.3747 0.03024 0.02256 -0.0447 0.0560 1.0000
11.500 1.3845 0.03153 0.02390 -0.0436 0.0550 1.0000
11.750 1.3937 0.03289 0.02531 -0.0426 0.0540 1.0000
12.000 1.4018 0.03440 0.02687 -0.0416 0.0531 1.0000
12.250 1.4096 0.03596 0.02848 -0.0407 0.0524 1.0000
12.500 1.4154 0.03774 0.03031 -0.0397 0.0512 1.0000
12.750 1.4209 0.03961 0.03224 -0.0389 0.0504 1.0000
13.000 1.4260 0.04157 0.03427 -0.0382 0.0497 1.0000
13.250 1.4311 0.04356 0.03632 -0.0376 0.0492 1.0000
13.500 1.4387 0.04535 0.03819 -0.0371 0.0487 1.0000
13.750 1.4457 0.04724 0.04015 -0.0367 0.0483 1.0000
14.000 1.4517 0.04928 0.04226 -0.0363 0.0476 1.0000
14.250 1.4572 0.05140 0.04446 -0.0360 0.0469 1.0000
14.500 1.4616 0.05366 0.04679 -0.0358 0.0462 1.0000
14.750 1.4644 0.05614 0.04934 -0.0356 0.0451 1.0000
15.000 1.4664 0.05878 0.05204 -0.0355 0.0445 1.0000
15.250 1.4669 0.06162 0.05496 -0.0355 0.0436 1.0000
15.500 1.4657 0.06468 0.05808 -0.0355 0.0426 1.0000
15.750 1.4665 0.06753 0.06101 -0.0356 0.0419 1.0000
16.000 1.4703 0.07004 0.06360 -0.0357 0.0408 1.0000
16.250 1.4717 0.07287 0.06651 -0.0359 0.0397 1.0000
16.500 1.4717 0.07591 0.06960 -0.0362 0.0375 1.0000
16.750 1.4689 0.07934 0.07309 -0.0366 0.0366 1.0000
17.000 1.4681 0.08254 0.07637 -0.0370 0.0340 1.0000
17.250 1.4578 0.08707 0.08086 -0.0378 0.0200 1.0000
17.500 1.4357 0.09339 0.08720 -0.0391 0.0157 1.0000
17.750 1.4210 0.09881 0.09272 -0.0404 0.0147 1.0000
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