GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Reynolds number: 50,000 Max Cl/Cd: 21.12 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe217-il-50000-n5.txt Download as CSV file: xf-goe217-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 217 (MVA MK.12) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1962 0.12572 0.11851 -0.0461 1.0000 0.0817
-11.000 -0.2010 0.12355 0.11647 -0.0453 1.0000 0.0808
-10.750 -0.2113 0.12175 0.11481 -0.0438 1.0000 0.0800
-10.500 -0.2011 0.11686 0.10994 -0.0484 0.9918 0.0794
-10.250 -0.1890 0.11112 0.10419 -0.0541 0.9804 0.0787
-10.000 -0.2043 0.10041 0.09344 -0.0631 0.9683 0.0760
-9.750 -0.1944 0.09447 0.08748 -0.0685 0.9559 0.0754
-9.500 -0.1924 0.08712 0.08008 -0.0751 0.9437 0.0744
-9.250 -0.2284 0.07440 0.06712 -0.0866 0.9288 0.0723
-9.000 -0.2709 0.06317 0.05539 -0.0993 0.9073 0.0707
-8.750 -0.2669 0.05647 0.04823 -0.1101 0.8919 0.0703
-8.500 -0.2469 0.05260 0.04403 -0.1161 0.8774 0.0703
-8.250 -0.2244 0.05000 0.04120 -0.1193 0.8630 0.0705
-8.000 -0.1937 0.04778 0.03876 -0.1219 0.8526 0.0708
-7.750 -0.1724 0.04631 0.03715 -0.1222 0.8370 0.0712
-7.500 -0.1468 0.04497 0.03568 -0.1224 0.8244 0.0718
-7.250 -0.1214 0.04385 0.03443 -0.1223 0.8119 0.0724
-7.000 -0.0985 0.04291 0.03338 -0.1219 0.7985 0.0734
-6.750 -0.0714 0.04187 0.03217 -0.1220 0.7877 0.0749
-6.500 -0.0490 0.04110 0.03128 -0.1217 0.7742 0.0763
-6.250 -0.0232 0.04040 0.03058 -0.1209 0.7646 0.0778
-6.000 -0.0018 0.03985 0.03003 -0.1204 0.7516 0.0793
-5.750 0.0260 0.03909 0.02916 -0.1206 0.7424 0.0808
-5.500 0.0498 0.03854 0.02855 -0.1209 0.7303 0.0821
-5.250 0.0793 0.03775 0.02767 -0.1220 0.7211 0.0837
-5.000 0.1081 0.03687 0.02678 -0.1241 0.7110 0.0858
-4.750 0.1402 0.03587 0.02572 -0.1268 0.7014 0.0886
-4.500 0.1789 0.03453 0.02427 -0.1310 0.6942 0.0931
-4.250 0.2150 0.03325 0.02305 -0.1359 0.6833 0.1012
-4.000 0.2629 0.03122 0.02186 -0.1439 0.6752 0.1931
-3.750 0.2979 0.03111 0.02175 -0.1458 0.6675 0.2511
-3.500 0.3295 0.03132 0.02190 -0.1471 0.6586 0.2840
-3.250 0.3590 0.03184 0.02234 -0.1468 0.6520 0.3076
-3.000 0.3875 0.03253 0.02293 -0.1462 0.6457 0.3294
-2.750 0.4119 0.03338 0.02376 -0.1454 0.6374 0.3468
-2.500 0.4402 0.03397 0.02422 -0.1451 0.6309 0.3636
-2.250 0.4715 0.03443 0.02449 -0.1452 0.6259 0.3811
-2.000 0.4833 0.03606 0.02626 -0.1406 0.6189 0.3897
-1.750 0.5068 0.03692 0.02710 -0.1396 0.6127 0.4054
-1.500 0.5323 0.03745 0.02755 -0.1386 0.6076 0.4168
-1.250 0.5664 0.03725 0.02716 -0.1400 0.6035 0.4256
-1.000 0.5885 0.03772 0.02764 -0.1395 0.5972 0.4310
-0.750 0.6240 0.03760 0.02736 -0.1429 0.5909 0.4435
-0.500 0.6470 0.03798 0.02772 -0.1416 0.5862 0.4482
0.000 0.7089 0.03826 0.02776 -0.1435 0.5785 0.4674
0.250 0.7240 0.03926 0.02888 -0.1420 0.5724 0.4729
0.500 0.7506 0.03974 0.02931 -0.1427 0.5672 0.4832
0.750 0.7787 0.04001 0.02952 -0.1429 0.5630 0.4917
1.000 0.8071 0.04021 0.02965 -0.1427 0.5597 0.5000
1.250 0.8347 0.04089 0.03027 -0.1439 0.5555 0.5116
1.500 0.8428 0.04240 0.03195 -0.1418 0.5495 0.5167
1.750 0.8628 0.04326 0.03284 -0.1413 0.5446 0.5253
2.000 0.8927 0.04364 0.03314 -0.1421 0.5407 0.5357
2.250 0.9202 0.04383 0.03331 -0.1416 0.5377 0.5433
2.500 0.9380 0.04513 0.03463 -0.1414 0.5330 0.5525
2.750 0.9370 0.04762 0.03729 -0.1397 0.5255 0.5583
3.000 0.9539 0.04852 0.03824 -0.1385 0.5208 0.5643
3.250 0.9857 0.04868 0.03833 -0.1391 0.5173 0.5735
3.500 1.0234 0.04846 0.03802 -0.1402 0.5147 0.5819
3.750 0.9791 0.05394 0.04382 -0.1353 0.5024 0.5830
4.000 1.0070 0.05397 0.04383 -0.1350 0.4976 0.5900
4.250 1.0590 0.05261 0.04229 -0.1371 0.4943 0.6004
4.750 1.0314 0.05848 0.04840 -0.1310 0.4756 0.6063
5.000 1.0867 0.05632 0.04612 -0.1323 0.4728 0.6152
5.500 1.0605 0.06372 0.05369 -0.1291 0.4532 0.6222
5.750 1.1079 0.06142 0.05132 -0.1287 0.4510 0.6294
6.250 1.0322 0.07599 0.06621 -0.1277 0.4206 0.6318
6.500 1.0528 0.07669 0.06689 -0.1274 0.4141 0.6378
6.750 1.0872 0.07524 0.06540 -0.1264 0.4111 0.6440
7.000 1.1287 0.07303 0.06314 -0.1255 0.4092 0.6514
7.500 1.1291 0.07900 0.06920 -0.1250 0.3897 0.6590
8.000 1.0790 0.09188 0.08228 -0.1257 0.3584 0.6621
8.250 1.1075 0.09113 0.08151 -0.1249 0.3546 0.6686
8.750 1.1159 0.09642 0.08685 -0.1247 0.3368 0.6769
9.250 1.1227 0.10210 0.09258 -0.1247 0.3198 0.6852
9.750 1.1255 0.10867 0.09921 -0.1253 0.3035 0.6926
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Polar data table (+)
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