GOE 600 AIRFOIL (goe600-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 600 AIRFOIL (goe600-il) Reynolds number: 500,000 Max Cl/Cd: 91.25 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe600-il-500000.txt Download as CSV file: xf-goe600-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 600 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8983 0.08606 0.08313 -0.0307 1.0000 0.0147
-15.000 -0.9405 0.07381 0.07059 -0.0390 1.0000 0.0145
-14.750 -0.9630 0.06592 0.06251 -0.0444 1.0000 0.0144
-14.500 -0.9801 0.05938 0.05579 -0.0488 1.0000 0.0144
-14.250 -0.9934 0.05376 0.04999 -0.0525 1.0000 0.0145
-14.000 -1.0027 0.04899 0.04508 -0.0554 1.0000 0.0146
-13.750 -1.0087 0.04494 0.04088 -0.0576 1.0000 0.0147
-13.500 -1.0115 0.04159 0.03740 -0.0592 1.0000 0.0149
-13.250 -1.0126 0.03873 0.03442 -0.0601 1.0000 0.0151
-13.000 -1.0123 0.03635 0.03191 -0.0603 1.0000 0.0153
-12.750 -1.0104 0.03440 0.02983 -0.0596 1.0000 0.0155
-12.500 -1.0080 0.03272 0.02803 -0.0582 1.0000 0.0158
-12.250 -1.0043 0.03131 0.02649 -0.0562 1.0000 0.0162
-12.000 -0.9962 0.02991 0.02495 -0.0546 1.0000 0.0166
-11.750 -0.9850 0.02859 0.02346 -0.0532 1.0000 0.0170
-11.500 -0.9714 0.02743 0.02213 -0.0519 1.0000 0.0174
-11.250 -0.9615 0.02554 0.02007 -0.0502 1.0000 0.0178
-11.000 -0.9489 0.02410 0.01856 -0.0487 1.0000 0.0183
-10.750 -0.9331 0.02320 0.01762 -0.0474 1.0000 0.0189
-10.500 -0.9178 0.02243 0.01680 -0.0458 1.0000 0.0194
-10.250 -0.9047 0.02171 0.01601 -0.0436 1.0000 0.0201
-10.000 -0.8946 0.02107 0.01529 -0.0409 1.0000 0.0207
-9.750 -0.8794 0.02047 0.01458 -0.0390 0.9994 0.0213
-9.500 -0.8496 0.01914 0.01318 -0.0405 0.9965 0.0226
-9.250 -0.8158 0.01846 0.01248 -0.0425 0.9941 0.0239
-9.000 -0.7830 0.01780 0.01176 -0.0440 0.9907 0.0254
-8.750 -0.7503 0.01698 0.01083 -0.0456 0.9873 0.0269
-8.500 -0.7170 0.01615 0.01001 -0.0474 0.9846 0.0291
-8.250 -0.6833 0.01570 0.00951 -0.0489 0.9809 0.0315
-8.000 -0.6535 0.01494 0.00872 -0.0498 0.9750 0.0345
-7.750 -0.6206 0.01451 0.00827 -0.0512 0.9703 0.0378
-7.500 -0.5938 0.01393 0.00763 -0.0512 0.9618 0.0412
-7.250 -0.5659 0.01346 0.00715 -0.0514 0.9549 0.0453
-7.000 -0.5405 0.01322 0.00683 -0.0509 0.9452 0.0484
-6.750 -0.5175 0.01256 0.00615 -0.0501 0.9364 0.0536
-6.500 -0.4929 0.01224 0.00576 -0.0495 0.9271 0.0575
-6.250 -0.4688 0.01179 0.00529 -0.0488 0.9176 0.0637
-5.750 -0.4190 0.01105 0.00465 -0.0476 0.8986 0.0916
-5.500 -0.3931 0.01081 0.00447 -0.0473 0.8896 0.1153
-5.250 -0.3665 0.01062 0.00427 -0.0470 0.8802 0.1303
-5.000 -0.3394 0.01045 0.00407 -0.0469 0.8709 0.1406
-4.750 -0.3124 0.01030 0.00386 -0.0466 0.8623 0.1497
-4.500 -0.2851 0.01007 0.00364 -0.0466 0.8523 0.1585
-4.000 -0.2305 0.00966 0.00320 -0.0464 0.8345 0.1814
-3.750 -0.2038 0.00928 0.00297 -0.0464 0.8263 0.2172
-3.500 -0.1776 0.00880 0.00278 -0.0464 0.8181 0.2997
-3.250 -0.1504 0.00850 0.00264 -0.0464 0.8106 0.3549
-3.000 -0.1230 0.00825 0.00253 -0.0464 0.8030 0.4046
-2.750 -0.0952 0.00809 0.00245 -0.0465 0.7958 0.4433
-2.500 -0.0672 0.00796 0.00239 -0.0465 0.7878 0.4766
-2.250 -0.0393 0.00786 0.00234 -0.0465 0.7801 0.5087
-2.000 -0.0112 0.00777 0.00230 -0.0465 0.7723 0.5399
-1.750 0.0171 0.00772 0.00227 -0.0466 0.7652 0.5636
-1.500 0.0456 0.00767 0.00224 -0.0467 0.7579 0.5837
-1.250 0.0741 0.00766 0.00221 -0.0467 0.7515 0.6028
-1.000 0.1026 0.00760 0.00220 -0.0468 0.7441 0.6198
-0.750 0.1309 0.00758 0.00217 -0.0469 0.7380 0.6382
-0.500 0.1594 0.00752 0.00219 -0.0470 0.7319 0.6588
-0.250 0.1877 0.00747 0.00219 -0.0470 0.7261 0.6804
0.000 0.2160 0.00745 0.00220 -0.0470 0.7207 0.7011
0.250 0.2442 0.00738 0.00223 -0.0471 0.7146 0.7249
0.500 0.2719 0.00732 0.00226 -0.0469 0.7089 0.7534
0.750 0.2993 0.00727 0.00230 -0.0467 0.7031 0.7852
1.000 0.3261 0.00719 0.00236 -0.0463 0.6967 0.8207
1.250 0.3517 0.00716 0.00242 -0.0455 0.6907 0.8625
1.500 0.3766 0.00709 0.00249 -0.0445 0.6835 0.9057
1.750 0.4040 0.00711 0.00252 -0.0440 0.6754 0.9404
2.000 0.4376 0.00712 0.00256 -0.0451 0.6646 0.9625
2.250 0.4743 0.00717 0.00258 -0.0469 0.6542 0.9773
2.500 0.5132 0.00724 0.00261 -0.0493 0.6442 0.9878
2.750 0.5549 0.00729 0.00267 -0.0523 0.6319 0.9953
3.000 0.5936 0.00735 0.00271 -0.0548 0.6187 1.0000
3.250 0.6183 0.00739 0.00273 -0.0542 0.6066 1.0000
3.500 0.6431 0.00745 0.00276 -0.0537 0.5927 1.0000
3.750 0.6680 0.00753 0.00281 -0.0531 0.5754 1.0000
4.000 0.6924 0.00766 0.00286 -0.0524 0.5521 1.0000
4.250 0.7163 0.00785 0.00295 -0.0517 0.5186 1.0000
4.500 0.7390 0.00818 0.00309 -0.0508 0.4753 1.0000
4.750 0.7617 0.00858 0.00330 -0.0500 0.4370 1.0000
5.000 0.7846 0.00900 0.00356 -0.0492 0.4031 1.0000
5.250 0.8084 0.00937 0.00380 -0.0487 0.3755 1.0000
5.750 0.8573 0.01003 0.00430 -0.0477 0.3292 1.0000
6.000 0.8814 0.01039 0.00456 -0.0472 0.3055 1.0000
6.250 0.9054 0.01077 0.00484 -0.0467 0.2785 1.0000
6.500 0.9289 0.01119 0.00515 -0.0461 0.2518 1.0000
6.750 0.9519 0.01164 0.00549 -0.0455 0.2259 1.0000
7.000 0.9744 0.01213 0.00586 -0.0448 0.2006 1.0000
7.250 0.9967 0.01264 0.00625 -0.0441 0.1752 1.0000
7.500 1.0184 0.01318 0.00668 -0.0433 0.1507 1.0000
7.750 1.0397 0.01375 0.00713 -0.0425 0.1278 1.0000
8.000 1.0605 0.01434 0.00761 -0.0416 0.1060 1.0000
8.250 1.0806 0.01497 0.00814 -0.0406 0.0894 1.0000
8.500 1.1006 0.01558 0.00870 -0.0395 0.0748 1.0000
8.750 1.1188 0.01633 0.00933 -0.0382 0.0540 1.0000
9.000 1.1354 0.01715 0.01003 -0.0367 0.0408 1.0000
9.250 1.1527 0.01789 0.01078 -0.0352 0.0358 1.0000
9.500 1.1677 0.01874 0.01163 -0.0335 0.0325 1.0000
9.750 1.1814 0.01953 0.01250 -0.0314 0.0303 1.0000
10.000 1.1945 0.02027 0.01330 -0.0293 0.0286 1.0000
10.250 1.2054 0.02118 0.01426 -0.0271 0.0271 1.0000
10.500 1.2089 0.02264 0.01577 -0.0241 0.0255 1.0000
10.750 1.2221 0.02351 0.01673 -0.0225 0.0245 1.0000
11.000 1.2345 0.02448 0.01777 -0.0209 0.0234 1.0000
11.250 1.2452 0.02560 0.01895 -0.0193 0.0224 1.0000
11.500 1.2534 0.02694 0.02035 -0.0177 0.0215 1.0000
11.750 1.2548 0.02889 0.02235 -0.0156 0.0207 1.0000
12.000 1.2596 0.03065 0.02421 -0.0139 0.0202 1.0000
12.250 1.2696 0.03202 0.02568 -0.0128 0.0196 1.0000
12.500 1.2782 0.03356 0.02731 -0.0118 0.0190 1.0000
12.750 1.2859 0.03520 0.02903 -0.0108 0.0184 1.0000
13.000 1.2929 0.03695 0.03085 -0.0099 0.0178 1.0000
13.250 1.2986 0.03886 0.03282 -0.0092 0.0173 1.0000
13.500 1.3004 0.04117 0.03519 -0.0083 0.0168 1.0000
13.750 1.2956 0.04420 0.03829 -0.0069 0.0163 1.0000
14.000 1.3014 0.04627 0.04048 -0.0066 0.0160 1.0000
14.250 1.3051 0.04857 0.04291 -0.0061 0.0157 1.0000
14.500 1.3074 0.05107 0.04553 -0.0058 0.0154 1.0000
14.750 1.3088 0.05373 0.04830 -0.0056 0.0151 1.0000
15.000 1.3092 0.05656 0.05124 -0.0055 0.0148 1.0000
15.250 1.3090 0.05956 0.05436 -0.0056 0.0145 1.0000
15.500 1.3081 0.06274 0.05764 -0.0059 0.0143 1.0000
15.750 1.3067 0.06608 0.06108 -0.0065 0.0140 1.0000
16.000 1.3044 0.06959 0.06468 -0.0071 0.0138 1.0000
16.250 1.3015 0.07327 0.06846 -0.0079 0.0136 1.0000
16.500 1.2978 0.07713 0.07240 -0.0088 0.0134 1.0000
16.750 1.2927 0.08121 0.07657 -0.0098 0.0132 1.0000
17.000 1.2843 0.08572 0.08118 -0.0106 0.0130 1.0000
17.250 1.2727 0.09098 0.08661 -0.0121 0.0129 1.0000
17.500 1.2638 0.09639 0.09218 -0.0146 0.0128 1.0000
17.750 1.2537 0.10209 0.09804 -0.0173 0.0127 1.0000
18.000 1.2426 0.10807 0.10418 -0.0203 0.0126 1.0000
18.250 1.2305 0.11438 0.11065 -0.0235 0.0125 1.0000
18.500 1.2174 0.12107 0.11751 -0.0272 0.0125 1.0000
18.750 1.2033 0.12811 0.12471 -0.0311 0.0124 1.0000
19.000 1.1878 0.13561 0.13236 -0.0355 0.0123 1.0000
19.250 1.1710 0.14367 0.14059 -0.0404 0.0123 1.0000
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