GOE 632 AIRFOIL (goe632-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 632 AIRFOIL (goe632-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.62 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe632-il-1000000-n5.txt Download as CSV file: xf-goe632-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 632 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9514 0.03684 0.03400 -0.0915 1.0000 0.0198
-14.500 -0.9670 0.03447 0.03148 -0.0884 1.0000 0.0199
-14.250 -0.9755 0.03285 0.02973 -0.0848 1.0000 0.0201
-13.750 -0.9649 0.02961 0.02621 -0.0817 0.9968 0.0203
-13.500 -0.9567 0.02835 0.02481 -0.0798 0.9886 0.0204
-13.250 -0.9437 0.02703 0.02335 -0.0786 0.9811 0.0206
-13.000 -0.9259 0.02591 0.02209 -0.0781 0.9720 0.0206
-12.750 -0.9019 0.02474 0.02078 -0.0786 0.9619 0.0207
-12.500 -0.8718 0.02301 0.01886 -0.0809 0.9520 0.0209
-12.250 -0.8309 0.02163 0.01736 -0.0851 0.9419 0.0213
-12.000 -0.7871 0.02067 0.01627 -0.0895 0.9248 0.0215
-11.750 -0.7519 0.01995 0.01538 -0.0918 0.8943 0.0217
-11.500 -0.7328 0.01951 0.01477 -0.0905 0.8643 0.0219
-11.000 -0.7020 0.01866 0.01364 -0.0861 0.8291 0.0222
-10.750 -0.6859 0.01813 0.01299 -0.0840 0.8182 0.0223
-10.250 -0.6499 0.01724 0.01190 -0.0805 0.8005 0.0226
-9.750 -0.6110 0.01645 0.01093 -0.0774 0.7839 0.0231
-9.500 -0.5914 0.01603 0.01040 -0.0759 0.7755 0.0233
-9.250 -0.5708 0.01559 0.00988 -0.0745 0.7671 0.0235
-9.000 -0.5502 0.01521 0.00940 -0.0731 0.7585 0.0236
-8.750 -0.5288 0.01480 0.00891 -0.0719 0.7493 0.0238
-8.500 -0.5076 0.01444 0.00845 -0.0706 0.7400 0.0239
-8.250 -0.4857 0.01409 0.00801 -0.0694 0.7292 0.0241
-8.000 -0.4637 0.01376 0.00760 -0.0682 0.7186 0.0243
-7.750 -0.4417 0.01347 0.00721 -0.0670 0.7067 0.0244
-7.500 -0.4192 0.01320 0.00686 -0.0659 0.6942 0.0245
-7.250 -0.3965 0.01294 0.00652 -0.0648 0.6826 0.0246
-7.000 -0.3740 0.01269 0.00618 -0.0636 0.6707 0.0248
-6.750 -0.3522 0.01231 0.00572 -0.0624 0.6601 0.0250
-6.500 -0.3297 0.01198 0.00533 -0.0613 0.6513 0.0254
-6.250 -0.3065 0.01174 0.00503 -0.0603 0.6431 0.0257
-6.000 -0.2826 0.01152 0.00477 -0.0595 0.6363 0.0260
-5.750 -0.2583 0.01134 0.00456 -0.0587 0.6300 0.0263
-5.250 -0.2095 0.01098 0.00412 -0.0571 0.6192 0.0270
-5.000 -0.1849 0.01080 0.00391 -0.0564 0.6135 0.0273
-4.750 -0.1606 0.01065 0.00372 -0.0556 0.6079 0.0277
-4.500 -0.1357 0.01048 0.00352 -0.0549 0.6035 0.0279
-4.250 -0.1105 0.01033 0.00335 -0.0543 0.5990 0.0283
-4.000 -0.0858 0.01020 0.00318 -0.0535 0.5936 0.0286
-3.750 -0.0610 0.01008 0.00303 -0.0528 0.5887 0.0289
-3.500 -0.0355 0.00996 0.00288 -0.0522 0.5844 0.0292
-3.250 -0.0105 0.00981 0.00272 -0.0516 0.5796 0.0296
-3.000 0.0142 0.00968 0.00257 -0.0508 0.5748 0.0305
-2.750 0.0394 0.00957 0.00246 -0.0502 0.5701 0.0313
-2.500 0.0649 0.00947 0.00235 -0.0496 0.5657 0.0320
-2.250 0.0901 0.00939 0.00226 -0.0490 0.5609 0.0329
-2.000 0.1150 0.00933 0.00218 -0.0483 0.5556 0.0341
-1.750 0.1405 0.00923 0.00209 -0.0477 0.5509 0.0359
-1.500 0.1656 0.00916 0.00202 -0.0471 0.5452 0.0383
-1.250 0.1903 0.00911 0.00196 -0.0463 0.5398 0.0421
-1.000 0.2155 0.00903 0.00192 -0.0457 0.5350 0.0488
-0.750 0.2403 0.00897 0.00189 -0.0450 0.5276 0.0577
-0.500 0.2649 0.00896 0.00187 -0.0443 0.5194 0.0636
-0.250 0.2884 0.00896 0.00184 -0.0433 0.5055 0.0691
0.000 0.3128 0.00897 0.00182 -0.0426 0.4942 0.0729
0.250 0.3362 0.00900 0.00181 -0.0416 0.4801 0.0774
0.500 0.3597 0.00901 0.00180 -0.0407 0.4697 0.0838
0.750 0.3827 0.00904 0.00181 -0.0396 0.4580 0.0928
1.000 0.4037 0.00886 0.00181 -0.0383 0.4495 0.1612
1.250 0.4218 0.00864 0.00183 -0.0363 0.4411 0.2596
1.500 0.4395 0.00840 0.00187 -0.0343 0.4330 0.3693
1.750 0.4572 0.00828 0.00192 -0.0322 0.4223 0.4433
2.000 0.4444 0.00728 0.00184 -0.0235 0.4152 0.7454
2.250 0.4882 0.00707 0.00212 -0.0269 0.4038 0.9153
2.500 0.5307 0.00726 0.00227 -0.0303 0.3939 0.9292
2.750 0.5752 0.00747 0.00243 -0.0341 0.3828 0.9341
3.000 0.6022 0.00764 0.00255 -0.0339 0.3742 0.9409
3.250 0.6304 0.00779 0.00267 -0.0340 0.3669 0.9458
3.500 0.6619 0.00799 0.00282 -0.0350 0.3576 0.9480
3.750 0.6899 0.00824 0.00298 -0.0351 0.3438 0.9511
4.000 0.7043 0.00836 0.00309 -0.0322 0.3371 0.9583
4.250 0.7352 0.00860 0.00326 -0.0330 0.3254 0.9593
4.500 0.7670 0.00882 0.00343 -0.0341 0.3159 0.9606
4.750 0.7996 0.00910 0.00366 -0.0353 0.3042 0.9626
5.000 0.8277 0.00934 0.00385 -0.0356 0.2943 0.9646
5.250 0.8510 0.00961 0.00405 -0.0349 0.2797 0.9671
5.500 0.8666 0.00984 0.00423 -0.0324 0.2668 0.9716
5.750 0.8893 0.01051 0.00465 -0.0320 0.2199 0.9728
6.000 0.9101 0.01135 0.00522 -0.0314 0.1713 0.9747
6.250 0.9365 0.01169 0.00552 -0.0315 0.1611 0.9765
6.500 0.9601 0.01199 0.00578 -0.0310 0.1537 0.9788
6.750 0.9731 0.01227 0.00604 -0.0281 0.1476 0.9831
7.000 1.0007 0.01248 0.00625 -0.0285 0.1430 0.9838
7.250 1.0247 0.01285 0.00655 -0.0283 0.1307 0.9849
7.750 1.0649 0.01384 0.00734 -0.0267 0.0942 0.9882
8.000 1.0854 0.01423 0.00769 -0.0258 0.0889 0.9900
8.250 1.1054 0.01463 0.00808 -0.0249 0.0845 0.9919
8.500 1.1254 0.01497 0.00843 -0.0240 0.0827 0.9936
8.750 1.1497 0.01530 0.00878 -0.0240 0.0809 0.9945
9.000 1.1729 0.01567 0.00916 -0.0239 0.0794 0.9955
9.250 1.1950 0.01608 0.00959 -0.0236 0.0779 0.9967
9.500 1.2161 0.01656 0.01007 -0.0233 0.0760 0.9979
9.750 1.2375 0.01705 0.01058 -0.0231 0.0741 0.9989
10.000 1.2591 0.01758 0.01113 -0.0230 0.0727 0.9997
10.250 1.2734 0.01806 0.01165 -0.0214 0.0718 1.0000
10.500 1.2830 0.01855 0.01217 -0.0188 0.0713 1.0000
10.750 1.2926 0.01907 0.01274 -0.0164 0.0706 1.0000
11.000 1.3020 0.01967 0.01338 -0.0140 0.0698 1.0000
11.250 1.3109 0.02035 0.01408 -0.0118 0.0677 1.0000
11.500 1.3186 0.02115 0.01490 -0.0095 0.0654 1.0000
11.750 1.3251 0.02207 0.01584 -0.0072 0.0631 1.0000
12.000 1.3339 0.02293 0.01672 -0.0053 0.0611 1.0000
12.250 1.3421 0.02387 0.01768 -0.0035 0.0570 1.0000
12.500 1.3236 0.02666 0.02026 0.0004 0.0306 1.0000
12.750 1.3131 0.02914 0.02272 0.0032 0.0192 1.0000
13.000 1.3154 0.03079 0.02440 0.0048 0.0170 1.0000
13.250 1.3181 0.03248 0.02614 0.0063 0.0154 1.0000
13.500 1.3210 0.03421 0.02791 0.0076 0.0143 1.0000
13.750 1.3252 0.03590 0.02966 0.0087 0.0135 1.0000
14.000 1.3294 0.03765 0.03145 0.0097 0.0130 1.0000
14.250 1.3326 0.03952 0.03338 0.0107 0.0124 1.0000
14.500 1.3356 0.04148 0.03539 0.0115 0.0121 1.0000
14.750 1.3370 0.04364 0.03761 0.0123 0.0115 1.0000
15.000 1.3402 0.04568 0.03970 0.0130 0.0110 1.0000
15.250 1.3438 0.04770 0.04177 0.0135 0.0109 1.0000
15.500 1.3460 0.04991 0.04405 0.0140 0.0107 1.0000
15.750 1.3481 0.05219 0.04638 0.0144 0.0103 1.0000
16.000 1.3504 0.05446 0.04871 0.0148 0.0102 1.0000
16.250 1.3502 0.05706 0.05137 0.0151 0.0096 1.0000
16.500 1.3507 0.05962 0.05400 0.0152 0.0095 1.0000
16.750 1.3505 0.06231 0.05675 0.0153 0.0093 1.0000
17.000 1.3490 0.06520 0.05970 0.0153 0.0090 1.0000
17.250 1.3472 0.06819 0.06275 0.0153 0.0088 1.0000
17.500 1.3466 0.07105 0.06569 0.0151 0.0087 1.0000
17.750 1.3463 0.07391 0.06861 0.0149 0.0086 1.0000
18.000 1.3452 0.07693 0.07170 0.0146 0.0084 1.0000
18.250 1.3432 0.08012 0.07496 0.0142 0.0083 1.0000
18.500 1.3420 0.08319 0.07810 0.0137 0.0081 1.0000
18.750 1.3399 0.08641 0.08139 0.0132 0.0078 1.0000
19.000 1.3356 0.08999 0.08505 0.0125 0.0078 1.0000
19.250 1.3323 0.09347 0.08860 0.0118 0.0076 1.0000
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Polar data table (+)
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