GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 604 AIRFOIL (goe604-il) Reynolds number: 500,000 Max Cl/Cd: 85.68 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe604-il-500000-n5.txt Download as CSV file: xf-goe604-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 604 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.6784 0.08985 0.08650 -0.0667 1.0000 0.0217
-16.750 -0.7014 0.08277 0.07933 -0.0708 1.0000 0.0218
-16.500 -0.7261 0.07582 0.07228 -0.0749 1.0000 0.0220
-16.250 -0.7526 0.06897 0.06533 -0.0789 1.0000 0.0220
-16.000 -0.7778 0.06239 0.05865 -0.0827 1.0000 0.0222
-15.750 -0.8038 0.05582 0.05197 -0.0866 1.0000 0.0223
-15.500 -0.8257 0.04973 0.04575 -0.0903 1.0000 0.0224
-15.250 -0.8442 0.04400 0.03990 -0.0940 1.0000 0.0225
-15.000 -0.8592 0.03888 0.03464 -0.0974 1.0000 0.0227
-14.750 -0.8735 0.03488 0.03052 -0.0993 1.0000 0.0228
-14.250 -0.8560 0.02977 0.02515 -0.1044 0.9836 0.0237
-14.000 -0.8387 0.02802 0.02325 -0.1064 0.9744 0.0242
-13.750 -0.8161 0.02643 0.02154 -0.1087 0.9663 0.0246
-13.500 -0.7885 0.02507 0.02012 -0.1112 0.9571 0.0250
-13.250 -0.7588 0.02401 0.01898 -0.1134 0.9458 0.0256
-13.000 -0.7295 0.02306 0.01793 -0.1152 0.9317 0.0261
-12.750 -0.7059 0.02227 0.01703 -0.1155 0.9141 0.0267
-12.500 -0.6883 0.02162 0.01623 -0.1144 0.8930 0.0273
-12.250 -0.6722 0.02105 0.01550 -0.1128 0.8695 0.0278
-12.000 -0.6576 0.02051 0.01478 -0.1108 0.8422 0.0282
-11.750 -0.6449 0.01997 0.01409 -0.1085 0.8114 0.0286
-11.500 -0.6304 0.01956 0.01352 -0.1064 0.7800 0.0291
-11.250 -0.6142 0.01921 0.01302 -0.1044 0.7514 0.0296
-11.000 -0.5971 0.01888 0.01252 -0.1026 0.7254 0.0302
-10.750 -0.5794 0.01854 0.01202 -0.1009 0.7028 0.0308
-10.500 -0.5603 0.01822 0.01155 -0.0993 0.6830 0.0314
-10.000 -0.5208 0.01748 0.01056 -0.0965 0.6527 0.0326
-9.750 -0.5004 0.01710 0.01011 -0.0952 0.6413 0.0332
-9.500 -0.4789 0.01679 0.00971 -0.0941 0.6298 0.0338
-9.250 -0.4565 0.01648 0.00933 -0.0931 0.6201 0.0346
-9.000 -0.4342 0.01619 0.00894 -0.0920 0.6108 0.0353
-8.750 -0.4109 0.01590 0.00857 -0.0911 0.6029 0.0360
-8.500 -0.3876 0.01562 0.00821 -0.0901 0.5947 0.0367
-8.250 -0.3651 0.01527 0.00780 -0.0891 0.5877 0.0376
-8.000 -0.3413 0.01497 0.00746 -0.0883 0.5804 0.0384
-7.750 -0.3175 0.01474 0.00715 -0.0874 0.5734 0.0392
-7.500 -0.2928 0.01450 0.00686 -0.0867 0.5668 0.0403
-7.250 -0.2681 0.01428 0.00657 -0.0859 0.5595 0.0413
-7.000 -0.2442 0.01404 0.00625 -0.0851 0.5524 0.0423
-6.750 -0.2194 0.01378 0.00597 -0.0844 0.5458 0.0435
-6.500 -0.1943 0.01357 0.00572 -0.0837 0.5396 0.0448
-6.250 -0.1693 0.01341 0.00548 -0.0830 0.5343 0.0462
-6.000 -0.1436 0.01320 0.00524 -0.0824 0.5292 0.0479
-5.750 -0.1182 0.01299 0.00502 -0.0818 0.5236 0.0500
-5.500 -0.0927 0.01284 0.00481 -0.0811 0.5184 0.0523
-5.250 -0.0670 0.01267 0.00461 -0.0805 0.5141 0.0548
-5.000 -0.0411 0.01249 0.00442 -0.0800 0.5094 0.0582
-4.750 -0.0154 0.01233 0.00424 -0.0794 0.5040 0.0624
-4.500 0.0101 0.01220 0.00407 -0.0788 0.4990 0.0681
-4.250 0.0358 0.01200 0.00390 -0.0783 0.4945 0.0771
-4.000 0.0611 0.01177 0.00374 -0.0777 0.4899 0.0934
-3.750 0.0864 0.01159 0.00366 -0.0771 0.4852 0.1201
-3.500 0.1124 0.01154 0.00359 -0.0766 0.4807 0.1344
-3.250 0.1391 0.01145 0.00353 -0.0762 0.4764 0.1450
-3.000 0.1657 0.01140 0.00346 -0.0758 0.4713 0.1526
-2.750 0.1918 0.01135 0.00340 -0.0752 0.4660 0.1601
-2.500 0.2182 0.01134 0.00335 -0.0748 0.4612 0.1657
-2.250 0.2446 0.01126 0.00329 -0.0744 0.4564 0.1741
-2.000 0.2709 0.01123 0.00325 -0.0739 0.4514 0.1824
-1.750 0.2964 0.01119 0.00322 -0.0733 0.4466 0.1931
-1.500 0.3225 0.01113 0.00319 -0.0729 0.4421 0.2072
-1.250 0.3484 0.01106 0.00318 -0.0724 0.4370 0.2265
-1.000 0.3738 0.01102 0.00317 -0.0718 0.4318 0.2476
-0.750 0.3992 0.01100 0.00318 -0.0713 0.4269 0.2664
-0.500 0.4252 0.01097 0.00318 -0.0708 0.4215 0.2848
-0.250 0.4506 0.01096 0.00319 -0.0702 0.4157 0.3029
0.000 0.4756 0.01097 0.00322 -0.0696 0.4104 0.3216
0.250 0.5012 0.01096 0.00324 -0.0691 0.4052 0.3416
0.500 0.5262 0.01096 0.00328 -0.0685 0.3998 0.3635
0.750 0.5503 0.01098 0.00333 -0.0677 0.3949 0.3898
1.000 0.5751 0.01093 0.00338 -0.0671 0.3903 0.4243
1.250 0.5988 0.01088 0.00344 -0.0662 0.3853 0.4664
1.500 0.6211 0.01082 0.00351 -0.0652 0.3805 0.5200
1.750 0.6426 0.01073 0.00360 -0.0639 0.3758 0.5876
2.000 0.6625 0.01059 0.00370 -0.0623 0.3701 0.6675
2.250 0.6801 0.01047 0.00382 -0.0601 0.3643 0.7542
2.500 0.7012 0.01037 0.00397 -0.0585 0.3593 0.8446
2.750 0.7657 0.01055 0.00428 -0.0661 0.3526 0.9351
3.000 0.8247 0.01085 0.00451 -0.0728 0.3469 0.9630
3.250 0.8645 0.01106 0.00467 -0.0754 0.3430 0.9767
3.500 0.8996 0.01123 0.00483 -0.0770 0.3395 0.9861
3.750 0.9337 0.01144 0.00499 -0.0785 0.3354 0.9940
4.000 0.9745 0.01168 0.00518 -0.0814 0.3313 1.0000
4.250 0.9921 0.01187 0.00533 -0.0795 0.3279 1.0000
4.500 1.0116 0.01200 0.00545 -0.0780 0.3248 1.0000
4.750 1.0305 0.01215 0.00560 -0.0763 0.3216 1.0000
5.000 1.0491 0.01232 0.00575 -0.0746 0.3189 1.0000
5.250 1.0670 0.01251 0.00592 -0.0728 0.3163 1.0000
5.500 1.0844 0.01272 0.00611 -0.0709 0.3138 1.0000
5.750 1.1008 0.01293 0.00630 -0.0688 0.3116 1.0000
6.000 1.1180 0.01308 0.00647 -0.0668 0.3098 1.0000
6.250 1.1349 0.01325 0.00665 -0.0649 0.3076 1.0000
6.500 1.1516 0.01344 0.00685 -0.0629 0.3052 1.0000
6.750 1.1681 0.01366 0.00706 -0.0609 0.3025 1.0000
7.000 1.1844 0.01391 0.00731 -0.0590 0.3001 1.0000
7.250 1.2004 0.01419 0.00758 -0.0571 0.2975 1.0000
7.500 1.2172 0.01448 0.00787 -0.0554 0.2949 1.0000
7.750 1.2361 0.01471 0.00813 -0.0541 0.2926 1.0000
8.000 1.2547 0.01498 0.00842 -0.0527 0.2902 1.0000
8.250 1.2723 0.01528 0.00875 -0.0513 0.2873 1.0000
8.500 1.2891 0.01564 0.00910 -0.0498 0.2844 1.0000
8.750 1.3051 0.01604 0.00951 -0.0483 0.2818 1.0000
9.000 1.3214 0.01645 0.00993 -0.0469 0.2790 1.0000
9.250 1.3399 0.01679 0.01032 -0.0458 0.2759 1.0000
9.500 1.3571 0.01720 0.01076 -0.0446 0.2727 1.0000
9.750 1.3731 0.01768 0.01126 -0.0433 0.2695 1.0000
10.000 1.3874 0.01826 0.01184 -0.0419 0.2663 1.0000
10.250 1.4028 0.01882 0.01243 -0.0407 0.2634 1.0000
10.500 1.4195 0.01934 0.01300 -0.0397 0.2597 1.0000
10.750 1.4343 0.01998 0.01367 -0.0386 0.2556 1.0000
11.000 1.4458 0.02082 0.01453 -0.0373 0.2511 1.0000
11.250 1.4599 0.02157 0.01532 -0.0363 0.2466 1.0000
11.500 1.4720 0.02247 0.01624 -0.0352 0.2407 1.0000
11.750 1.4809 0.02362 0.01741 -0.0340 0.2346 1.0000
12.000 1.4903 0.02480 0.01861 -0.0330 0.2269 1.0000
12.250 1.4940 0.02647 0.02027 -0.0318 0.2166 1.0000
12.500 1.4919 0.02868 0.02245 -0.0305 0.2033 1.0000
12.750 1.4833 0.03159 0.02532 -0.0292 0.1895 1.0000
13.000 1.4784 0.03433 0.02806 -0.0283 0.1819 1.0000
13.250 1.4753 0.03700 0.03076 -0.0276 0.1762 1.0000
13.500 1.4681 0.04013 0.03390 -0.0270 0.1708 1.0000
13.750 1.4652 0.04290 0.03673 -0.0266 0.1670 1.0000
14.000 1.4645 0.04552 0.03940 -0.0262 0.1645 1.0000
14.250 1.4597 0.04857 0.04250 -0.0260 0.1613 1.0000
14.500 1.4542 0.05175 0.04573 -0.0257 0.1588 1.0000
14.750 1.4482 0.05505 0.04907 -0.0256 0.1563 1.0000
15.000 1.4492 0.05766 0.05176 -0.0256 0.1545 1.0000
15.250 1.4506 0.06021 0.05437 -0.0256 0.1530 1.0000
15.500 1.4497 0.06306 0.05730 -0.0257 0.1512 1.0000
15.750 1.4498 0.06583 0.06013 -0.0258 0.1500 1.0000
16.000 1.4470 0.06895 0.06331 -0.0259 0.1482 1.0000
16.250 1.4409 0.07250 0.06690 -0.0262 0.1459 1.0000
16.500 1.4387 0.07558 0.07003 -0.0264 0.1444 1.0000
16.750 1.4347 0.07893 0.07343 -0.0268 0.1426 1.0000
17.000 1.4387 0.08137 0.07595 -0.0271 0.1412 1.0000
17.250 1.4391 0.08426 0.07893 -0.0275 0.1392 1.0000
17.500 1.4401 0.08706 0.08179 -0.0279 0.1374 1.0000
17.750 1.4381 0.09026 0.08506 -0.0284 0.1355 1.0000
18.000 1.4357 0.09352 0.08836 -0.0290 0.1334 1.0000
18.250 1.4328 0.09687 0.09176 -0.0296 0.1318 1.0000
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