GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 604 AIRFOIL (goe604-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.81 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe604-il-1000000-n5.txt Download as CSV file: xf-goe604-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.8181 0.08397 0.08102 -0.0709 1.0000 0.0171
-17.750 -0.8637 0.07426 0.07117 -0.0769 1.0000 0.0169
-17.500 -0.9248 0.06279 0.05951 -0.0841 1.0000 0.0167
-17.250 -0.9865 0.05126 0.04778 -0.0916 1.0000 0.0166
-17.000 -1.0310 0.04127 0.03756 -0.0990 1.0000 0.0165
-16.750 -1.0528 0.03465 0.03076 -0.1043 1.0000 0.0166
-16.500 -1.0647 0.03078 0.02676 -0.1064 1.0000 0.0168
-16.250 -1.0718 0.02841 0.02431 -0.1061 1.0000 0.0170
-15.750 -1.0530 0.02509 0.02081 -0.1070 0.9859 0.0176
-15.500 -1.0318 0.02394 0.01958 -0.1081 0.9781 0.0180
-15.250 -1.0065 0.02277 0.01835 -0.1099 0.9708 0.0184
-15.000 -0.9747 0.02175 0.01728 -0.1123 0.9645 0.0189
-14.750 -0.9394 0.02083 0.01631 -0.1151 0.9570 0.0194
-14.500 -0.9045 0.02001 0.01541 -0.1176 0.9454 0.0199
-14.250 -0.8758 0.01933 0.01465 -0.1187 0.9290 0.0204
-14.000 -0.8573 0.01882 0.01400 -0.1175 0.9080 0.0208
-13.750 -0.8442 0.01841 0.01348 -0.1152 0.8869 0.0210
-13.500 -0.8307 0.01796 0.01293 -0.1130 0.8647 0.0215
-13.250 -0.8161 0.01759 0.01244 -0.1107 0.8382 0.0219
-13.000 -0.8010 0.01728 0.01199 -0.1085 0.8078 0.0223
-12.750 -0.7853 0.01703 0.01157 -0.1064 0.7733 0.0227
-12.500 -0.7685 0.01677 0.01116 -0.1044 0.7409 0.0232
-12.250 -0.7500 0.01652 0.01077 -0.1027 0.7148 0.0236
-12.000 -0.7305 0.01626 0.01039 -0.1012 0.6921 0.0240
-11.750 -0.7100 0.01601 0.01002 -0.0998 0.6727 0.0244
-11.500 -0.6901 0.01568 0.00959 -0.0984 0.6556 0.0248
-11.250 -0.6691 0.01537 0.00921 -0.0971 0.6406 0.0253
-10.750 -0.6239 0.01485 0.00856 -0.0951 0.6185 0.0264
-10.500 -0.6008 0.01462 0.00825 -0.0941 0.6087 0.0269
-10.250 -0.5772 0.01436 0.00793 -0.0932 0.5999 0.0273
-9.750 -0.5291 0.01390 0.00734 -0.0915 0.5841 0.0282
-9.500 -0.5056 0.01361 0.00700 -0.0906 0.5766 0.0289
-9.250 -0.4813 0.01337 0.00672 -0.0898 0.5698 0.0295
-9.000 -0.4564 0.01315 0.00646 -0.0891 0.5633 0.0302
-8.750 -0.4314 0.01296 0.00621 -0.0884 0.5563 0.0308
-8.500 -0.4062 0.01276 0.00597 -0.0877 0.5504 0.0314
-8.250 -0.3806 0.01258 0.00573 -0.0871 0.5434 0.0319
-8.000 -0.3557 0.01240 0.00549 -0.0864 0.5353 0.0325
-7.750 -0.3303 0.01217 0.00524 -0.0857 0.5290 0.0333
-7.500 -0.3046 0.01199 0.00502 -0.0851 0.5229 0.0341
-7.250 -0.2790 0.01183 0.00482 -0.0845 0.5175 0.0349
-7.000 -0.2527 0.01168 0.00463 -0.0840 0.5125 0.0357
-6.750 -0.2262 0.01154 0.00445 -0.0835 0.5076 0.0365
-6.500 -0.2003 0.01136 0.00425 -0.0829 0.5029 0.0376
-6.000 -0.1476 0.01108 0.00392 -0.0819 0.4941 0.0399
-5.750 -0.1209 0.01095 0.00377 -0.0815 0.4891 0.0411
-5.500 -0.0946 0.01083 0.00362 -0.0810 0.4840 0.0427
-5.250 -0.0682 0.01071 0.00348 -0.0805 0.4797 0.0449
-5.000 -0.0412 0.01060 0.00335 -0.0801 0.4761 0.0470
-4.750 -0.0146 0.01047 0.00322 -0.0797 0.4718 0.0498
-4.500 0.0121 0.01038 0.00311 -0.0793 0.4670 0.0528
-4.250 0.0384 0.01028 0.00300 -0.0788 0.4621 0.0569
-4.000 0.0653 0.01016 0.00289 -0.0784 0.4579 0.0618
-3.750 0.0917 0.01005 0.00278 -0.0779 0.4527 0.0692
-3.500 0.1175 0.00991 0.00266 -0.0774 0.4477 0.0820
-3.250 0.1429 0.00971 0.00257 -0.0768 0.4436 0.1086
-3.000 0.1695 0.00960 0.00252 -0.0764 0.4392 0.1272
-2.750 0.1965 0.00957 0.00248 -0.0761 0.4342 0.1356
-2.500 0.2230 0.00954 0.00245 -0.0756 0.4290 0.1432
-2.250 0.2503 0.00953 0.00242 -0.0753 0.4247 0.1484
-2.000 0.2772 0.00950 0.00239 -0.0750 0.4191 0.1552
-1.750 0.3036 0.00950 0.00238 -0.0746 0.4129 0.1610
-1.500 0.3307 0.00951 0.00236 -0.0742 0.4079 0.1652
-1.250 0.3571 0.00948 0.00235 -0.0738 0.4019 0.1750
-1.000 0.3832 0.00948 0.00235 -0.0734 0.3961 0.1857
-0.750 0.4096 0.00945 0.00235 -0.0730 0.3915 0.1992
-0.250 0.4613 0.00941 0.00238 -0.0720 0.3804 0.2376
0.000 0.4874 0.00941 0.00240 -0.0715 0.3758 0.2556
0.250 0.5135 0.00941 0.00243 -0.0711 0.3709 0.2732
0.500 0.5390 0.00945 0.00247 -0.0706 0.3647 0.2902
0.750 0.5645 0.00948 0.00252 -0.0701 0.3586 0.3069
1.000 0.5899 0.00952 0.00258 -0.0695 0.3514 0.3242
1.250 0.6146 0.00959 0.00265 -0.0689 0.3447 0.3420
1.500 0.6402 0.00960 0.00270 -0.0684 0.3408 0.3620
2.000 0.6895 0.00962 0.00285 -0.0671 0.3324 0.4222
2.250 0.7131 0.00963 0.00294 -0.0663 0.3283 0.4615
2.500 0.7371 0.00958 0.00301 -0.0655 0.3257 0.5102
2.750 0.7600 0.00952 0.00310 -0.0646 0.3226 0.5692
3.000 0.7812 0.00943 0.00321 -0.0633 0.3191 0.6439
3.250 0.8001 0.00934 0.00333 -0.0615 0.3152 0.7240
3.500 0.8165 0.00921 0.00346 -0.0590 0.3123 0.8169
3.750 0.8502 0.00912 0.00367 -0.0602 0.3100 0.9240
4.000 0.9273 0.00939 0.00393 -0.0709 0.3056 0.9626
4.250 0.9708 0.00959 0.00410 -0.0743 0.3022 0.9739
4.500 1.0037 0.00978 0.00426 -0.0755 0.2993 0.9825
4.750 1.0374 0.00998 0.00443 -0.0770 0.2962 0.9902
5.000 1.0763 0.01016 0.00460 -0.0795 0.2943 0.9978
5.250 1.1144 0.01033 0.00476 -0.0818 0.2920 1.0000
5.500 1.1338 0.01045 0.00488 -0.0802 0.2898 1.0000
5.750 1.1529 0.01060 0.00502 -0.0786 0.2872 1.0000
6.000 1.1710 0.01078 0.00517 -0.0768 0.2840 1.0000
6.250 1.1888 0.01097 0.00535 -0.0750 0.2810 1.0000
6.500 1.2069 0.01112 0.00550 -0.0732 0.2790 1.0000
6.750 1.2238 0.01125 0.00565 -0.0711 0.2770 1.0000
7.000 1.2404 0.01140 0.00580 -0.0690 0.2743 1.0000
7.250 1.2570 0.01158 0.00597 -0.0670 0.2714 1.0000
7.500 1.2740 0.01179 0.00618 -0.0652 0.2687 1.0000
7.750 1.2908 0.01202 0.00640 -0.0633 0.2659 1.0000
8.000 1.3092 0.01224 0.00663 -0.0618 0.2636 1.0000
8.250 1.3285 0.01244 0.00685 -0.0605 0.2612 1.0000
8.500 1.3474 0.01268 0.00709 -0.0592 0.2582 1.0000
8.750 1.3648 0.01298 0.00739 -0.0576 0.2540 1.0000
9.000 1.3813 0.01334 0.00773 -0.0561 0.2491 1.0000
9.250 1.3994 0.01365 0.00805 -0.0548 0.2442 1.0000
9.500 1.4158 0.01405 0.00844 -0.0533 0.2387 1.0000
9.750 1.4316 0.01450 0.00888 -0.0518 0.2329 1.0000
10.000 1.4455 0.01505 0.00940 -0.0502 0.2243 1.0000
10.250 1.4575 0.01572 0.01003 -0.0483 0.2133 1.0000
10.500 1.4617 0.01681 0.01103 -0.0457 0.1960 1.0000
10.750 1.4655 0.01801 0.01216 -0.0433 0.1821 1.0000
11.000 1.4709 0.01920 0.01332 -0.0413 0.1725 1.0000
11.250 1.4788 0.02034 0.01445 -0.0397 0.1664 1.0000
11.500 1.4862 0.02157 0.01568 -0.0382 0.1613 1.0000
11.750 1.4927 0.02293 0.01705 -0.0369 0.1566 1.0000
12.000 1.5036 0.02406 0.01822 -0.0360 0.1543 1.0000
12.250 1.5135 0.02531 0.01950 -0.0352 0.1522 1.0000
12.500 1.5231 0.02663 0.02086 -0.0344 0.1507 1.0000
12.750 1.5291 0.02829 0.02255 -0.0336 0.1482 1.0000
13.000 1.5341 0.03010 0.02440 -0.0329 0.1458 1.0000
13.250 1.5388 0.03200 0.02635 -0.0323 0.1437 1.0000
13.500 1.5453 0.03378 0.02818 -0.0318 0.1421 1.0000
13.750 1.5528 0.03549 0.02996 -0.0315 0.1410 1.0000
14.000 1.5589 0.03737 0.03190 -0.0312 0.1398 1.0000
14.250 1.5634 0.03943 0.03400 -0.0308 0.1384 1.0000
14.500 1.5640 0.04187 0.03649 -0.0305 0.1358 1.0000
14.750 1.5634 0.04447 0.03914 -0.0302 0.1339 1.0000
15.000 1.5612 0.04728 0.04200 -0.0299 0.1320 1.0000
15.250 1.5591 0.05010 0.04489 -0.0297 0.1305 1.0000
15.500 1.5594 0.05272 0.04756 -0.0296 0.1293 1.0000
15.750 1.5625 0.05505 0.04996 -0.0296 0.1280 1.0000
16.000 1.5618 0.05784 0.05282 -0.0296 0.1262 1.0000
16.250 1.5610 0.06065 0.05569 -0.0296 0.1247 1.0000
16.500 1.5567 0.06386 0.05894 -0.0297 0.1220 1.0000
16.750 1.5510 0.06732 0.06245 -0.0299 0.1202 1.0000
17.000 1.5432 0.07104 0.06622 -0.0301 0.1175 1.0000
17.250 1.5428 0.07390 0.06914 -0.0304 0.1156 1.0000
17.500 1.5371 0.07745 0.07275 -0.0307 0.1126 1.0000
17.750 1.5275 0.08151 0.07685 -0.0312 0.1090 1.0000
18.000 1.5184 0.08553 0.08089 -0.0317 0.1047 1.0000
18.250 1.4978 0.09103 0.08639 -0.0325 0.0958 1.0000
18.500 1.4741 0.09707 0.09243 -0.0335 0.0858 1.0000
18.750 1.4372 0.10492 0.10023 -0.0350 0.0703 1.0000
19.000 1.4148 0.11101 0.10632 -0.0364 0.0616 1.0000
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