GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 398 AIRFOIL (goe398-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.53 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe398-il-1000000-n5.txt Download as CSV file: xf-goe398-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 398 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7027 0.09496 0.09263 -0.0642 1.0000 0.0151
-16.250 -1.0752 0.03398 0.03061 -0.1094 1.0000 0.0135
-16.000 -1.1031 0.03085 0.02734 -0.1078 1.0000 0.0135
-15.250 -1.0623 0.02576 0.02195 -0.1098 0.9897 0.0143
-15.000 -1.0404 0.02455 0.02065 -0.1105 0.9862 0.0146
-14.750 -1.0160 0.02350 0.01952 -0.1113 0.9838 0.0150
-14.500 -0.9983 0.02261 0.01855 -0.1105 0.9783 0.0153
-14.250 -0.9750 0.02174 0.01759 -0.1107 0.9743 0.0157
-14.000 -0.9505 0.02091 0.01667 -0.1109 0.9705 0.0159
-13.750 -0.9282 0.02012 0.01580 -0.1107 0.9640 0.0162
-13.500 -0.8986 0.01938 0.01502 -0.1117 0.9603 0.0167
-13.250 -0.8690 0.01875 0.01434 -0.1127 0.9555 0.0172
-13.000 -0.8361 0.01812 0.01366 -0.1142 0.9501 0.0176
-12.750 -0.7999 0.01748 0.01294 -0.1164 0.9449 0.0181
-12.500 -0.7667 0.01689 0.01226 -0.1180 0.9358 0.0185
-12.250 -0.7327 0.01634 0.01161 -0.1196 0.9258 0.0189
-12.000 -0.7032 0.01584 0.01101 -0.1202 0.9132 0.0194
-11.750 -0.6772 0.01546 0.01057 -0.1201 0.8998 0.0199
-11.500 -0.6528 0.01512 0.01015 -0.1195 0.8871 0.0203
-11.250 -0.6293 0.01483 0.00977 -0.1187 0.8746 0.0207
-11.000 -0.6068 0.01452 0.00937 -0.1177 0.8622 0.0211
-10.750 -0.5841 0.01423 0.00899 -0.1166 0.8514 0.0216
-10.500 -0.5615 0.01395 0.00861 -0.1156 0.8412 0.0219
-10.250 -0.5383 0.01367 0.00825 -0.1146 0.8325 0.0222
-9.750 -0.4928 0.01303 0.00749 -0.1126 0.8162 0.0231
-9.500 -0.4690 0.01280 0.00721 -0.1117 0.8083 0.0236
-9.250 -0.4449 0.01257 0.00692 -0.1108 0.8012 0.0241
-9.000 -0.4208 0.01234 0.00663 -0.1100 0.7926 0.0246
-8.750 -0.3970 0.01212 0.00633 -0.1090 0.7836 0.0250
-8.500 -0.3727 0.01192 0.00606 -0.1082 0.7738 0.0255
-8.250 -0.3483 0.01173 0.00579 -0.1073 0.7646 0.0258
-8.000 -0.3247 0.01144 0.00545 -0.1064 0.7562 0.0264
-7.750 -0.3004 0.01120 0.00517 -0.1055 0.7492 0.0269
-7.500 -0.2757 0.01099 0.00491 -0.1047 0.7403 0.0274
-7.250 -0.2511 0.01083 0.00469 -0.1039 0.7312 0.0280
-7.000 -0.2258 0.01066 0.00448 -0.1032 0.7229 0.0286
-6.750 -0.2010 0.01050 0.00425 -0.1024 0.7150 0.0291
-6.500 -0.1755 0.01033 0.00403 -0.1017 0.7068 0.0296
-6.250 -0.1507 0.01019 0.00383 -0.1009 0.6977 0.0301
-6.000 -0.1257 0.00999 0.00359 -0.1002 0.6886 0.0308
-5.750 -0.1009 0.00984 0.00340 -0.0994 0.6802 0.0316
-5.500 -0.0750 0.00969 0.00323 -0.0988 0.6731 0.0323
-5.250 -0.0495 0.00958 0.00306 -0.0981 0.6658 0.0330
-5.000 -0.0236 0.00946 0.00291 -0.0975 0.6593 0.0337
-4.750 0.0024 0.00936 0.00277 -0.0969 0.6520 0.0345
-4.250 0.0540 0.00911 0.00249 -0.0957 0.6404 0.0373
-4.000 0.0801 0.00902 0.00237 -0.0951 0.6340 0.0387
-3.750 0.1057 0.00894 0.00226 -0.0945 0.6276 0.0407
-3.500 0.1319 0.00883 0.00216 -0.0939 0.6211 0.0437
-3.250 0.1577 0.00876 0.00207 -0.0933 0.6137 0.0472
-3.000 0.1836 0.00868 0.00199 -0.0927 0.6079 0.0527
-2.750 0.2096 0.00859 0.00192 -0.0922 0.6007 0.0596
-2.250 0.2611 0.00847 0.00181 -0.0910 0.5853 0.0740
-2.000 0.2865 0.00843 0.00176 -0.0903 0.5767 0.0811
-1.750 0.3124 0.00839 0.00171 -0.0897 0.5676 0.0890
-1.500 0.3372 0.00836 0.00167 -0.0889 0.5568 0.0995
-1.250 0.3618 0.00831 0.00165 -0.0881 0.5435 0.1187
-1.000 0.3860 0.00826 0.00164 -0.0873 0.5289 0.1446
-0.750 0.4094 0.00829 0.00165 -0.0862 0.5096 0.1659
-0.500 0.4326 0.00835 0.00168 -0.0852 0.4895 0.1846
-0.250 0.4556 0.00845 0.00172 -0.0841 0.4680 0.2005
0.000 0.4785 0.00854 0.00177 -0.0830 0.4492 0.2162
0.250 0.5020 0.00861 0.00181 -0.0820 0.4353 0.2321
0.500 0.5257 0.00866 0.00186 -0.0811 0.4242 0.2515
0.750 0.5489 0.00861 0.00190 -0.0801 0.4150 0.2973
1.000 0.5705 0.00857 0.00198 -0.0788 0.4045 0.3638
1.250 0.5932 0.00844 0.00205 -0.0777 0.3986 0.4393
1.500 0.6151 0.00833 0.00212 -0.0764 0.3924 0.5151
1.750 0.6363 0.00826 0.00221 -0.0750 0.3868 0.5848
2.000 0.6559 0.00807 0.00229 -0.0732 0.3828 0.6791
2.250 0.6837 0.00758 0.00246 -0.0731 0.3770 0.9052
2.500 0.8096 0.00797 0.00280 -0.0949 0.3644 0.9770
2.750 0.8369 0.00811 0.00291 -0.0947 0.3583 0.9876
3.000 0.8736 0.00831 0.00305 -0.0967 0.3516 0.9948
3.250 0.9105 0.00844 0.00315 -0.0987 0.3458 0.9979
3.500 0.9473 0.00860 0.00326 -0.1008 0.3383 0.9998
3.750 0.9712 0.00874 0.00336 -0.1000 0.3325 1.0000
4.000 0.9931 0.00887 0.00347 -0.0987 0.3251 1.0000
4.250 1.0139 0.00905 0.00360 -0.0973 0.3173 1.0000
4.500 1.0353 0.00920 0.00373 -0.0960 0.3092 1.0000
4.750 1.0556 0.00940 0.00387 -0.0944 0.3011 1.0000
5.000 1.0764 0.00957 0.00402 -0.0930 0.2931 1.0000
5.250 1.0959 0.00979 0.00419 -0.0914 0.2846 1.0000
5.500 1.1149 0.01002 0.00437 -0.0896 0.2738 1.0000
5.750 1.1319 0.01032 0.00459 -0.0876 0.2592 1.0000
6.000 1.1491 0.01061 0.00482 -0.0855 0.2470 1.0000
6.250 1.1654 0.01089 0.00504 -0.0833 0.2375 1.0000
6.500 1.1801 0.01112 0.00525 -0.0807 0.2290 1.0000
6.750 1.1943 0.01139 0.00547 -0.0780 0.2206 1.0000
7.000 1.2093 0.01166 0.00571 -0.0756 0.2128 1.0000
7.250 1.2254 0.01192 0.00595 -0.0735 0.2069 1.0000
7.500 1.2429 0.01216 0.00618 -0.0716 0.2018 1.0000
7.750 1.2590 0.01247 0.00647 -0.0695 0.1957 1.0000
8.000 1.2767 0.01275 0.00675 -0.0678 0.1908 1.0000
8.250 1.2943 0.01304 0.00703 -0.0661 0.1861 1.0000
8.500 1.3105 0.01341 0.00738 -0.0642 0.1801 1.0000
8.750 1.3279 0.01374 0.00771 -0.0625 0.1749 1.0000
9.000 1.3443 0.01413 0.00808 -0.0608 0.1690 1.0000
9.250 1.3605 0.01454 0.00849 -0.0591 0.1639 1.0000
9.500 1.3780 0.01491 0.00887 -0.0576 0.1596 1.0000
9.750 1.3936 0.01538 0.00932 -0.0559 0.1541 1.0000
10.000 1.4095 0.01586 0.00980 -0.0543 0.1489 1.0000
10.250 1.4246 0.01638 0.01032 -0.0527 0.1423 1.0000
10.500 1.4370 0.01707 0.01097 -0.0508 0.1321 1.0000
10.750 1.4453 0.01801 0.01182 -0.0485 0.1163 1.0000
11.000 1.4346 0.02010 0.01365 -0.0441 0.0784 1.0000
11.250 1.4384 0.02145 0.01494 -0.0417 0.0656 1.0000
11.500 1.4463 0.02260 0.01609 -0.0398 0.0591 1.0000
11.750 1.4560 0.02368 0.01717 -0.0383 0.0555 1.0000
12.000 1.4675 0.02466 0.01818 -0.0369 0.0531 1.0000
12.250 1.4785 0.02571 0.01926 -0.0357 0.0514 1.0000
12.500 1.4877 0.02691 0.02049 -0.0344 0.0494 1.0000
12.750 1.4973 0.02812 0.02173 -0.0331 0.0477 1.0000
13.000 1.5078 0.02928 0.02294 -0.0321 0.0467 1.0000
13.250 1.5174 0.03055 0.02425 -0.0310 0.0456 1.0000
13.500 1.5260 0.03193 0.02567 -0.0300 0.0445 1.0000
13.750 1.5327 0.03350 0.02729 -0.0290 0.0430 1.0000
14.000 1.5388 0.03516 0.02899 -0.0280 0.0418 1.0000
14.250 1.5457 0.03680 0.03068 -0.0272 0.0411 1.0000
14.500 1.5534 0.03841 0.03235 -0.0265 0.0402 1.0000
14.750 1.5596 0.04019 0.03419 -0.0258 0.0391 1.0000
15.000 1.5641 0.04219 0.03623 -0.0251 0.0383 1.0000
15.250 1.5670 0.04437 0.03846 -0.0245 0.0373 1.0000
15.500 1.5692 0.04669 0.04083 -0.0240 0.0363 1.0000
15.750 1.5718 0.04902 0.04323 -0.0236 0.0356 1.0000
16.000 1.5755 0.05128 0.04556 -0.0233 0.0352 1.0000
16.250 1.5776 0.05375 0.04810 -0.0231 0.0344 1.0000
16.500 1.5783 0.05642 0.05085 -0.0230 0.0342 1.0000
16.750 1.5787 0.05917 0.05367 -0.0229 0.0335 1.0000
17.000 1.5777 0.06216 0.05673 -0.0230 0.0329 1.0000
17.250 1.5750 0.06538 0.06002 -0.0232 0.0324 1.0000
17.500 1.5700 0.06896 0.06366 -0.0235 0.0316 1.0000
17.750 1.5653 0.07258 0.06737 -0.0239 0.0314 1.0000
18.000 1.5590 0.07649 0.07136 -0.0245 0.0309 1.0000
18.250 1.5556 0.08002 0.07498 -0.0251 0.0303 1.0000
18.500 1.5500 0.08389 0.07894 -0.0258 0.0300 1.0000
18.750 1.5439 0.08788 0.08302 -0.0266 0.0296 1.0000
19.000 1.5368 0.09207 0.08730 -0.0276 0.0291 1.0000
19.250 1.5284 0.09644 0.09175 -0.0287 0.0286 1.0000
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