GOE 646 AIRFOIL (goe646-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 646 AIRFOIL (goe646-il) Reynolds number: 50,000 Max Cl/Cd: 5.16 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe646-il-50000.txt Download as CSV file: xf-goe646-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 646 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2639 0.13891 0.13151 -0.0273 1.0000 0.2868
-10.500 -0.2755 0.13835 0.13102 -0.0257 1.0000 0.2939
-10.250 -0.3176 0.14086 0.13367 -0.0240 1.0000 0.2969
-10.000 -0.2812 0.13405 0.12685 -0.0227 1.0000 0.3021
-9.750 -0.2804 0.13231 0.12515 -0.0209 1.0000 0.3091
-9.500 -0.3101 0.13327 0.12623 -0.0191 1.0000 0.3153
-9.250 -0.3196 0.13109 0.12413 -0.0176 1.0000 0.3179
-9.000 -0.2971 0.12730 0.12034 -0.0159 1.0000 0.3248
-8.750 -0.3131 0.12694 0.12006 -0.0139 1.0000 0.3333
-8.500 -0.3569 0.12857 0.12183 -0.0115 1.0000 0.3361
-8.250 -0.3234 0.12300 0.11625 -0.0104 1.0000 0.3420
-8.000 -0.3269 0.12177 0.11508 -0.0083 1.0000 0.3505
-7.750 -0.3698 0.12305 0.11649 -0.0057 1.0000 0.3560
-7.500 -0.3589 0.11935 0.11283 -0.0044 1.0000 0.3603
-7.250 -0.3511 0.11742 0.11092 -0.0026 1.0000 0.3687
-7.000 -0.3867 0.11788 0.11149 0.0002 1.0000 0.3760
-6.750 -0.4348 0.11843 0.11217 0.0033 1.0000 0.3776
-6.500 -0.5661 0.09727 0.09102 -0.0092 1.0000 0.2602
-6.250 -0.5795 0.09299 0.08672 -0.0095 1.0000 0.2587
-6.000 -0.5956 0.08773 0.08144 -0.0109 1.0000 0.2580
-5.750 -0.6140 0.08048 0.07409 -0.0148 1.0000 0.2575
-5.500 -0.6358 0.06772 0.06087 -0.0249 1.0000 0.2600
-5.000 -0.5984 0.06167 0.05435 -0.0312 0.9923 0.2780
-4.750 -0.5536 0.06546 0.05843 -0.0299 0.9786 0.2875
-4.500 -0.5399 0.05979 0.05230 -0.0356 0.9742 0.2990
-4.250 -0.5839 0.05674 0.04922 -0.0263 1.0000 0.2988
-4.000 -0.5715 0.05717 0.04977 -0.0237 1.0000 0.3059
-3.750 -0.5553 0.05417 0.04640 -0.0261 1.0000 0.3188
-3.500 -0.5421 0.05424 0.04655 -0.0242 1.0000 0.3275
-3.250 -0.5256 0.05253 0.04461 -0.0251 1.0000 0.3403
-3.000 -0.5098 0.05184 0.04378 -0.0248 1.0000 0.3531
-2.750 -0.4954 0.05144 0.04339 -0.0237 1.0000 0.3638
-2.500 -0.4773 0.05035 0.04202 -0.0246 1.0000 0.3793
-2.250 -0.4640 0.05054 0.04232 -0.0227 1.0000 0.3895
-2.000 -0.4473 0.04997 0.04162 -0.0227 1.0000 0.4035
-1.750 -0.4298 0.04965 0.04111 -0.0228 1.0000 0.4186
-1.500 -0.4166 0.04978 0.04137 -0.0210 1.0000 0.4292
-1.250 -0.3991 0.04949 0.04091 -0.0212 1.0000 0.4442
-1.000 -0.3844 0.04966 0.04111 -0.0200 1.0000 0.4565
-0.750 -0.3651 0.04986 0.04126 -0.0201 0.9986 0.4694
-0.500 -0.3328 0.05102 0.04225 -0.0227 0.9928 0.4863
-0.250 -0.3096 0.05173 0.04298 -0.0232 0.9864 0.4990
0.000 -0.2780 0.05327 0.04445 -0.0253 0.9794 0.5137
0.250 -0.2484 0.05406 0.04512 -0.0275 0.9689 0.5291
0.500 -0.2259 0.05484 0.04592 -0.0281 0.9600 0.5416
0.750 -0.1957 0.05633 0.04736 -0.0300 0.9506 0.5564
1.000 -0.1607 0.05804 0.04899 -0.0328 0.9373 0.5729
1.250 -0.1433 0.05827 0.04923 -0.0326 0.9251 0.5862
1.500 -0.1213 0.05927 0.05023 -0.0332 0.9144 0.5998
1.750 -0.0861 0.06140 0.05231 -0.0358 0.9023 0.6182
2.000 -0.0585 0.06241 0.05328 -0.0373 0.8864 0.6355
2.250 -0.0446 0.06290 0.05376 -0.0369 0.8747 0.6506
2.500 -0.0111 0.06505 0.05589 -0.0393 0.8640 0.6720
2.750 0.0262 0.06694 0.05779 -0.0419 0.8461 0.6962
3.000 0.0290 0.06673 0.05763 -0.0403 0.8355 0.7138
3.250 0.1533 0.06447 0.05546 -0.0461 0.7250 0.7836
3.500 0.2026 0.06476 0.05615 -0.0491 0.7097 0.8611
3.750 0.2784 0.06595 0.05724 -0.0602 0.6919 1.0000
4.000 0.2693 0.06792 0.05906 -0.0596 0.6829 1.0000
4.250 0.3105 0.06940 0.06025 -0.0627 0.6700 1.0000
4.500 0.3154 0.07132 0.06206 -0.0624 0.6610 1.0000
4.750 0.3436 0.07291 0.06348 -0.0634 0.6494 1.0000
5.000 0.3467 0.07516 0.06567 -0.0630 0.6431 1.0000
5.250 0.3790 0.07666 0.06703 -0.0641 0.6308 1.0000
5.500 0.3762 0.07917 0.06951 -0.0633 0.6258 1.0000
5.750 0.4152 0.08050 0.07072 -0.0645 0.6125 1.0000
6.000 0.4077 0.08340 0.07361 -0.0637 0.6096 1.0000
6.250 0.4080 0.08620 0.07640 -0.0635 0.6075 1.0000
6.500 0.4130 0.08945 0.07963 -0.0640 0.6101 1.0000
6.750 0.4316 0.09306 0.08322 -0.0655 0.6137 1.0000
7.000 0.4487 0.09403 0.08414 -0.0647 0.5929 1.0000
7.250 0.4753 0.09514 0.08519 -0.0645 0.5735 1.0000
7.500 0.4901 0.09879 0.08884 -0.0657 0.5759 1.0000
7.750 0.5143 0.09971 0.08971 -0.0651 0.5555 1.0000
8.000 0.4334 0.10761 0.09780 -0.0659 0.6195 1.0000
8.250 0.4571 0.11128 0.10144 -0.0672 0.6133 1.0000
8.500 0.4548 0.11246 0.10262 -0.0662 0.6014 1.0000
8.750 0.4948 0.11718 0.10732 -0.0685 0.5948 1.0000
9.000 0.4756 0.11746 0.10762 -0.0666 0.5842 1.0000
9.250 0.5137 0.12166 0.11180 -0.0684 0.5764 1.0000
9.500 0.5018 0.12324 0.11339 -0.0676 0.5713 1.0000
9.750 0.5119 0.12536 0.11552 -0.0678 0.5616 1.0000
10.000 0.5542 0.13079 0.12095 -0.0699 0.5560 1.0000
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Polar data table (+)
Polar graphs
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