GOE 600 AIRFOIL (goe600-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 600 AIRFOIL (goe600-il) Reynolds number: 500,000 Max Cl/Cd: 76.78 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe600-il-500000-n5.txt Download as CSV file: xf-goe600-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.8212 0.13945 0.13678 0.0013 1.0000 0.0082
-17.000 -0.8526 0.12801 0.12521 -0.0046 1.0000 0.0082
-16.750 -0.8815 0.11763 0.11472 -0.0100 1.0000 0.0081
-16.500 -0.9123 0.10725 0.10421 -0.0154 1.0000 0.0081
-16.250 -0.9433 0.09707 0.09388 -0.0207 1.0000 0.0080
-16.000 -0.9741 0.08723 0.08390 -0.0260 1.0000 0.0080
-15.750 -1.0029 0.07805 0.07457 -0.0312 1.0000 0.0079
-15.500 -1.0278 0.06969 0.06605 -0.0361 1.0000 0.0079
-15.250 -1.0487 0.06218 0.05837 -0.0407 1.0000 0.0079
-15.000 -1.0653 0.05556 0.05160 -0.0449 1.0000 0.0079
-14.750 -1.0779 0.04978 0.04566 -0.0487 1.0000 0.0080
-14.500 -1.0865 0.04486 0.04060 -0.0519 1.0000 0.0080
-14.250 -1.0911 0.04072 0.03632 -0.0545 1.0000 0.0081
-14.000 -1.0929 0.03729 0.03273 -0.0564 1.0000 0.0082
-13.750 -1.0926 0.03451 0.02982 -0.0574 1.0000 0.0083
-13.500 -1.0907 0.03225 0.02744 -0.0575 1.0000 0.0085
-13.250 -1.0876 0.03041 0.02549 -0.0568 1.0000 0.0086
-13.000 -1.0833 0.02892 0.02389 -0.0553 1.0000 0.0088
-12.750 -1.0779 0.02766 0.02252 -0.0533 1.0000 0.0089
-12.500 -1.0673 0.02650 0.02125 -0.0519 1.0000 0.0092
-12.250 -1.0539 0.02544 0.02008 -0.0507 1.0000 0.0095
-12.000 -1.0388 0.02448 0.01901 -0.0496 1.0000 0.0098
-11.750 -1.0223 0.02360 0.01801 -0.0485 1.0000 0.0100
-11.500 -1.0072 0.02256 0.01688 -0.0473 1.0000 0.0104
-11.250 -0.9913 0.02161 0.01586 -0.0461 1.0000 0.0108
-11.000 -0.9742 0.02083 0.01503 -0.0449 1.0000 0.0112
-10.750 -0.9489 0.02004 0.01415 -0.0453 0.9948 0.0117
-10.500 -0.9214 0.01927 0.01329 -0.0460 0.9878 0.0123
-10.250 -0.8934 0.01856 0.01247 -0.0468 0.9806 0.0128
-9.750 -0.8390 0.01714 0.01091 -0.0478 0.9641 0.0145
-9.500 -0.8126 0.01656 0.01027 -0.0480 0.9556 0.0156
-9.250 -0.7867 0.01605 0.00968 -0.0480 0.9470 0.0168
-9.000 -0.7623 0.01554 0.00911 -0.0476 0.9378 0.0182
-8.750 -0.7379 0.01507 0.00859 -0.0472 0.9292 0.0201
-8.500 -0.7132 0.01467 0.00813 -0.0468 0.9201 0.0221
-8.250 -0.6886 0.01428 0.00771 -0.0463 0.9118 0.0253
-8.000 -0.6633 0.01395 0.00733 -0.0460 0.9035 0.0285
-7.750 -0.6379 0.01361 0.00697 -0.0457 0.8959 0.0320
-7.500 -0.6117 0.01336 0.00664 -0.0454 0.8876 0.0347
-7.250 -0.5860 0.01301 0.00628 -0.0452 0.8795 0.0381
-7.000 -0.5598 0.01276 0.00597 -0.0450 0.8708 0.0413
-6.750 -0.5329 0.01253 0.00568 -0.0448 0.8621 0.0435
-6.500 -0.5069 0.01219 0.00529 -0.0446 0.8536 0.0473
-6.250 -0.4800 0.01192 0.00498 -0.0445 0.8444 0.0507
-6.000 -0.4529 0.01171 0.00469 -0.0444 0.8356 0.0535
-5.750 -0.4262 0.01141 0.00436 -0.0443 0.8259 0.0597
-5.500 -0.3992 0.01112 0.00407 -0.0443 0.8161 0.0681
-5.250 -0.3727 0.01078 0.00384 -0.0442 0.8062 0.0928
-5.000 -0.3450 0.01061 0.00365 -0.0442 0.7962 0.1064
-4.750 -0.3171 0.01047 0.00347 -0.0443 0.7872 0.1155
-4.250 -0.2611 0.01020 0.00312 -0.0444 0.7706 0.1283
-3.750 -0.2048 0.00994 0.00280 -0.0446 0.7558 0.1428
-3.500 -0.1765 0.00985 0.00266 -0.0447 0.7488 0.1490
-3.250 -0.1482 0.00971 0.00252 -0.0449 0.7427 0.1577
-3.000 -0.1200 0.00955 0.00238 -0.0451 0.7368 0.1707
-2.500 -0.0651 0.00892 0.00210 -0.0454 0.7244 0.2769
-2.250 -0.0374 0.00871 0.00200 -0.0455 0.7170 0.3231
-2.000 -0.0097 0.00846 0.00193 -0.0456 0.7099 0.3753
-1.750 0.0183 0.00829 0.00187 -0.0458 0.7035 0.4168
-1.500 0.0467 0.00819 0.00183 -0.0459 0.6978 0.4434
-1.250 0.0752 0.00810 0.00181 -0.0461 0.6913 0.4707
-0.750 0.1323 0.00798 0.00178 -0.0464 0.6785 0.5182
-0.500 0.1610 0.00795 0.00177 -0.0466 0.6723 0.5365
-0.250 0.1897 0.00792 0.00177 -0.0468 0.6671 0.5559
0.000 0.2185 0.00787 0.00178 -0.0470 0.6613 0.5746
0.250 0.2471 0.00786 0.00179 -0.0472 0.6556 0.5906
0.500 0.2759 0.00783 0.00181 -0.0474 0.6497 0.6057
0.750 0.3045 0.00780 0.00183 -0.0475 0.6431 0.6234
1.000 0.3329 0.00778 0.00186 -0.0476 0.6366 0.6433
1.250 0.3612 0.00772 0.00190 -0.0477 0.6287 0.6671
1.500 0.3890 0.00767 0.00193 -0.0477 0.6190 0.6975
1.750 0.4161 0.00761 0.00197 -0.0475 0.6028 0.7318
2.000 0.4430 0.00759 0.00202 -0.0472 0.5837 0.7644
2.250 0.4697 0.00758 0.00208 -0.0470 0.5662 0.7959
2.500 0.4956 0.00760 0.00216 -0.0464 0.5465 0.8316
2.750 0.5202 0.00765 0.00225 -0.0456 0.5194 0.8722
3.000 0.5439 0.00784 0.00237 -0.0446 0.4797 0.9133
3.250 0.5710 0.00816 0.00255 -0.0445 0.4384 0.9462
3.500 0.6029 0.00848 0.00273 -0.0455 0.4079 0.9681
3.750 0.6362 0.00873 0.00291 -0.0469 0.3863 0.9838
4.000 0.6702 0.00901 0.00310 -0.0485 0.3643 0.9948
4.250 0.7009 0.00926 0.00327 -0.0494 0.3452 1.0000
4.500 0.7255 0.00950 0.00345 -0.0489 0.3269 1.0000
4.750 0.7501 0.00977 0.00364 -0.0484 0.3059 1.0000
5.000 0.7743 0.01009 0.00385 -0.0479 0.2817 1.0000
5.250 0.7980 0.01048 0.00410 -0.0474 0.2525 1.0000
5.500 0.8221 0.01084 0.00436 -0.0469 0.2295 1.0000
5.750 0.8465 0.01118 0.00462 -0.0465 0.2112 1.0000
6.000 0.8709 0.01152 0.00490 -0.0460 0.1939 1.0000
6.250 0.8951 0.01187 0.00519 -0.0456 0.1778 1.0000
6.500 0.9190 0.01225 0.00551 -0.0451 0.1609 1.0000
6.750 0.9420 0.01270 0.00586 -0.0445 0.1409 1.0000
7.000 0.9647 0.01317 0.00624 -0.0438 0.1204 1.0000
7.250 0.9863 0.01372 0.00667 -0.0430 0.0990 1.0000
7.750 1.0315 0.01461 0.00749 -0.0417 0.0797 1.0000
8.000 1.0537 0.01507 0.00793 -0.0410 0.0724 1.0000
8.250 1.0761 0.01549 0.00835 -0.0403 0.0638 1.0000
8.500 1.0964 0.01605 0.00885 -0.0394 0.0486 1.0000
8.750 1.1146 0.01677 0.00945 -0.0381 0.0361 1.0000
9.000 1.1343 0.01734 0.01003 -0.0370 0.0316 1.0000
9.250 1.1530 0.01794 0.01064 -0.0358 0.0285 1.0000
9.500 1.1717 0.01851 0.01125 -0.0346 0.0262 1.0000
9.750 1.1899 0.01905 0.01185 -0.0333 0.0243 1.0000
10.000 1.2047 0.01968 0.01252 -0.0315 0.0224 1.0000
10.250 1.2186 0.02039 0.01327 -0.0296 0.0208 1.0000
10.500 1.2346 0.02100 0.01394 -0.0281 0.0195 1.0000
10.750 1.2494 0.02171 0.01470 -0.0266 0.0180 1.0000
11.000 1.2626 0.02256 0.01558 -0.0250 0.0166 1.0000
11.250 1.2761 0.02342 0.01650 -0.0235 0.0156 1.0000
11.500 1.2896 0.02430 0.01746 -0.0221 0.0147 1.0000
11.750 1.3021 0.02528 0.01849 -0.0208 0.0138 1.0000
12.000 1.3135 0.02637 0.01963 -0.0194 0.0131 1.0000
12.250 1.3225 0.02769 0.02100 -0.0180 0.0123 1.0000
12.500 1.3330 0.02892 0.02232 -0.0168 0.0119 1.0000
12.750 1.3428 0.03025 0.02374 -0.0156 0.0114 1.0000
13.000 1.3520 0.03167 0.02525 -0.0146 0.0108 1.0000
13.250 1.3602 0.03321 0.02687 -0.0136 0.0104 1.0000
13.500 1.3670 0.03492 0.02865 -0.0127 0.0100 1.0000
13.750 1.3719 0.03688 0.03069 -0.0119 0.0096 1.0000
14.000 1.3735 0.03921 0.03311 -0.0111 0.0093 1.0000
14.250 1.3766 0.04146 0.03547 -0.0105 0.0091 1.0000
14.500 1.3795 0.04380 0.03791 -0.0101 0.0089 1.0000
14.750 1.3811 0.04633 0.04056 -0.0097 0.0087 1.0000
15.000 1.3811 0.04908 0.04342 -0.0095 0.0085 1.0000
15.250 1.3801 0.05205 0.04651 -0.0095 0.0083 1.0000
15.500 1.3780 0.05527 0.04986 -0.0097 0.0081 1.0000
15.750 1.3749 0.05872 0.05342 -0.0101 0.0080 1.0000
16.000 1.3703 0.06251 0.05733 -0.0108 0.0078 1.0000
16.250 1.3651 0.06654 0.06148 -0.0117 0.0077 1.0000
16.500 1.3583 0.07093 0.06599 -0.0129 0.0076 1.0000
16.750 1.3501 0.07569 0.07087 -0.0144 0.0075 1.0000
17.000 1.3408 0.08080 0.07610 -0.0162 0.0074 1.0000
17.250 1.3300 0.08628 0.08171 -0.0183 0.0073 1.0000
17.500 1.3176 0.09213 0.08769 -0.0206 0.0072 1.0000
17.750 1.3040 0.09829 0.09398 -0.0232 0.0071 1.0000
18.000 1.2894 0.10472 0.10053 -0.0259 0.0071 1.0000
18.250 1.2749 0.11122 0.10715 -0.0288 0.0070 1.0000
18.500 1.2595 0.11795 0.11399 -0.0319 0.0070 1.0000
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